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  1. COMPARISON OF WIND TUNNEL AND FLIGHT TEST AFTERBODY AND NOZZLE PRESSURES FOR A TWIN-JET FIGHTER AIRCRAFT AT TRANSONIC SPEEDS , Technical Paper
    Authors: Jack Nugent and Odis C. Pendergraft, Jr.
    Report Number: NASA-TP-2588
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Afterbody and nozzle pressures measured on a 1/12-scale model and in flight on a twin-jet fighter aircraft were compared as Mach number varied from 0.6 to 1.2, Reynolds number from 17.5 million to 302.5 million, and angle of attack from 1 to 7 deg. At Mach 0.6 and 0.8, nozzle pressure coefficient distributions and nozzle axial force coefficients agreed and showed good recompression. At Mach 0.9 and 1.2, flow complexity caused a loss in recompression for both flight and wind tunnel nozzle data. The flight data exhibited less negative values of pressure coefficient and lower axial force coefficients than did the wind tunnel data. Reynolds number effects were noted only at these Mach numbers. Jet temperature and mass flux ratio did not affect the comparisons of nozzle axial flow coefficient. At subsonic speeds, the levels of pressure coefficient distributions on the upper fuselage and lower nacelle surfaces for flight were less negative than those for the model. The model boundary layer thickness at the aft rake station exceeded that for the forward rake station and increased with increasing angle of attack. The flight boundary layer thickness at the aft rake station was less than that for the forward rake station and decreased with increasing angle of attack.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 02
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    Report Date: March 1987
    No. Pages: 125
    Keywords:      Afterbodies; Fighter aircraft; Flight tests; Nozzle thrust coefficients; Transonic speed; Wind tunnel models; Wind tunnel tests


  2. USER'S MANUAL FOR LINEAR, A FORTRAN PROGRAM TO DERIVE LINEAR AIRCRAFT MODELS , Technical Paper
    Authors: Eugene L. Duke, Brian P. Patterson and Robert F. Antonievicz
    Report Number: NASA-TP-2768
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This report documents a FORTRAN program that provides a powerful and flexible tool for the linearization of aircraft models. The program LINEAR numerically determines a linear system model using nonlinear equations of motion and a user-supplied nonlinear aerodynamic model. The system model determined by LINEAR consists of matrices for both state and observation equations. The program has been designed to allow easy selection and definition of the state, control, and observation variables to be used in a particular model.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 66
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    Report Date: December 1987
    No. Pages: 109
    Keywords:      Aircraft models; Computer programs; FORTRAN; Linearization; Aerodynamics; Control systems design; Equations of motion; Equations of state


  3. QUALITATIVE EVALUATION OF A FLUSH AIR DATA SYSTEM AT TRANSONIC SPEEDS AND HIGH ANGLES OF ATTACK , Technical Paper
    Authors: Terry J.Larson, Stephen A. Whitmore, L. J.Ehernberger, J. Blair Johnson and Paul M. Siemers, III
    Report Number: NASA-TP-2716
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight tests were performed on an F-14 aircraft to evaluate the use of flush pressure orifices on the nose section for obtaining air data at transonic speeds over a large range of flow angles. This program was part of a flight test and wind tunnel program to assess the accuracies of such systems for general use on aircraft. It also provided data to validate algorithms developed for the shuttle entry air data system designed at NASA Langley. Data were obtained for Mach numbers between 0.60 and 1.60, for angles of attack up to 26.0 deg, and for sideslip angles up to 11.0 deg. With careful calibration, a flush air data system with all flush orifices can provide accurate air data information over a large range of flow angles. Several orificies on the nose cap were found to be suitable for determination of stagnation pressure. Other orifices on the nose section aft of the nose cap were shown to be suitable for determination of static pressure. Pairs of orifices on the nose cap provided the most sensitive measurements for determining angles of attack and sideslip, although orifices located farther aft on the nose section could also be used.
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    Subject Category: 05
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    Report Date: April 1987
    No. Pages: 64
    Keywords:      Air data systems; Angle of attack; Flow distribution; Orifice flow; Pitot tubes; Stagnation pressure; Transonic speed


  4. DIGITAL PROGRAM FOR CALCULATING STATIC PRESSURE POSITION ERROR , Technical Memorandum
    Authors: J. Blair Johnson, Terry J. Larson and Jules M. Ficke
    Report Number: NASA-TM-86726
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A computer program written to calculate the static pressure position error of airspeed systems contains five separate methods for determining position error, of which the user may select from one to five at a time. The program uses data from both the test aircraft and the ground-based radar to calculate the error. In addition, some of the methods require rawinsonde data or an atmospheric analysis, or both. The program output lists the corrections to Mach number, altitude, and static pressure that are due to position error. Reference values such as angle of attack, angle of sideslip, indicated Mach number, indicated pressure altitude, stagnation pressure, and total temperature are also listed.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    Report Date: February 1987
    No. Pages: 28
    Keywords:      Airspeed; Applications programs (computers); Errors; Position (location); Static pressure


  5. DESIGN AND INITIAL APPLICATION OF THE EXTENDEDAIRCRAFT INTERROGATION AND DISPLAY SYSTEM: MULTIPROCESSING GROUND SUPPORT EQUIPMENT FOR DIGITAL FLIGHT SYSTEMS , Technical Memorandum
    Authors: Richard D. Glover
    Report Number: NASA-TM-86740
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A pipelined, multiprocessor, general-purpose ground support equipment for digital flight systems has been developed and placed in service at the NASA Ames Research Center's Dryden Flight Research Facility. The design is an outgrowth of the earlier aircraft interrogation and display system (AIDS) used in support of several research projects to provide engineering-units display of internal control system parameters during development and qualification testing activities. The new system, incorporating multiple 16-bit processors, is called extended AIDS (XAIDS) and is now supporting the X-29A forward-swept-wing aircraft project. This report describes the design and mechanization of XAIDS and shows the steps whereby a typical user may take advantage of its high throughput and flexible features.
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    Subject Category: 05
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    Report Date: January 1987
    No. Pages: 93
    Keywords:      Data acquisition; Digital command systems; Display devices; Flight simulation; Flight tests; Interrogation


  6. HIGH-ANGLE-OF-ATTACK PNEUMATIC LAG AND UPWASH CORRECTIONS FOR A HEMISPHERICAL FLOW DIRECTION SENSOR , Technical Memorandum
    Authors: Stephen A. Whitmore (NASA Ames Research Center), Jennifer Heeg (NASA Ames Research Center), Terry J. Larson (NASA Ames Research Center), L. J. Ehernberger (NASA Ames Research Center), Floyd W. Hagen (NASA Ames Research Center) and Richard V. Deleo (NASA Ames Research Center)
    Report Number: NASA-TM-86790
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: As part of the NASA F-14 high angle of attack flight test program, a nose mounted hemispherical flow direction sensor was calibrated against a fuselage mounted movable vane flow angle sensor. Significant discrepancies were found to exist in the angle of attack measurements. A two fold approach taken to resolve these discrepancies during subsonic flight is described. First, the sensing integrity of the isolated hemispherical sensor is established by wind tunnel data extending to an angle of attack of 60 deg. Second, two probable causes for the discrepancies, pneumatic lag and upwash, are examined. Methods of identifying and compensating for lag and upwash are presented. The wind tunnel data verify that the isolated hemispherical sensor is sufficiently accurate for static conditions with angles of attack up to 60 deg and angles of sideslip up to 30 deg. Analysis of flight data for two high angle of attack maneuvers establishes that pneumatic lag and upwash are highly correlated with the discrepancies between the hemispherical and vane type sensor measurements.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 06
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    Report Date: May 1987
    No. Pages: 21
    Keywords:      Angle of attack; Flight tests; Flow distribution; Pneumatic probes; remote sensing; Time lag; Upwash


  7. HIGHLY INTEGRATED DIGITAL ELECTRONIC CONTROL:DIGITAL FLIGHT CONTROL, AIRCRAFT MODEL IDENTIFICATION,AND ADAPTIVE ENGINE CONTROL , Technical Memorandum
    Authors: Jennifer L. Baer-Riedhart (NASA Ames Research Center) and Robert J. Landy (McDonnell Aircraft Co.)
    Report Number: NASA-TM-86793
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The highly integrated digital electronic control (HIDEC) program at NASA Ames Research Center, Dryden Flight Research Facility is a multiphase flight research program to quantify the benefits of promising integrated control systems. McDonnell Aircraft Company is the prime contractor, with United Technologies Pratt and Whitney Aircraft, and Lear Siegler Incorporated as major subcontractors. The NASA F-15A testbed aircraft was modified by the HIDEC program by installing a digital electronic flight control system (DEFCS) and replacing the standard F100 (Arab 3) engines with F100 engine model derivative (EMD) engines equipped with digital electronic engine controls (DEEC), and integrating the DEEC's and DEFCS. The modified aircraft provides the capability for testing many integrated control modes involving the flight controls, engine controls, and inlet controls. This paper focuses on the first two phases of the HIDEC program, which are the digital flight control system/aircraft model identification (DEFCS/AMI) phase and the adaptive engine control system (ADECS) phase.
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    Subject Category: 07
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    Report Date: March 1987
    No. Pages: 16
    Keywords:      Adaptive control; Aircraft engines; Aircraft models; Digital electronics; Engine control; F-15 aircraft; Flight control; Flight tests; Identifying
    Notes: Presented at the AIAA Guidance and Control Conference, Snowmass, Colorado, August 19-21, 1985.


  8. A GENERAL SOLUTION TO THE SILHOUETTE PROBLEM , Technical Paper
    Authors: David R. Hedgley, Jr.
    Report Number: NASA-TP-2695
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: In displaying computer-generated graphics, it is advantageous to have the facility to render any subset of polygons as a silhouette with respect to itself. While the silhouette problem has been addressed before, there has been no completely general solution. In this report, the silhouette problem for calligraphic drawings is solved for the most general case. This solution offers all possible combinations of silhouette and non-silhouette specifications for an arbitrary solid. It allows the flexibility to enhance the clarity of any three-dimensional scene presented in two dimensions.
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    Subject Category: 59
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    Report Date: February 1987
    No. Pages: 9
    Keywords:      Computer graphics; Display devices; Image enhancement; Image processing; Dimensions; Engineering drawings; Polygons; Scene analysis; Set theory


  9. PREDICTION OF SERVICE LIFE OF AIRCRAFT STRUCTURAL COMPONENTS USING THE HALF-CYCLE METHOD , Technical Memorandum
    Authors: William L. Ko
    Report Number: NASA-TM-86812
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The service life of aircraft structural components undergoing random stress cycling was analyzed by the application of fracture mechanics. The initial crack sizes at the critical stress points for the fatigue-crack growth analysis were established through proof load tests. The fatigue-crack growth rates for random stress cycles were calculated using the half-cycle method. A new equation was developed for calculating the number of remaining flights for the structural components. The number of remaining flights predicted by the new equation is much lower than that predicted by the conventional equation.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 39
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    Report Date: May 1987
    No. Pages: 27
    Keywords:      Aircraft structures; Cyclic loads; Fatigue life; Predictions; Service life; Structural members


  10. COMPARISON OF MEASURED TEMPERATURES, THERMAL STRESSES AND CREEP RESIDUES WITH PREDICTIONS ON A BUILT-UP TITANIUM STRUCTURE , Technical Memorandum
    Authors: Jerald M. Jenkins
    Report Number: NASA-TM-86814
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Temperature, thermal stresses, and residual creep stresses were studied by comparing laboratory values measured on a built-up titanium structure with values calculated from finite-element models. Several such models were used to examine the relationship between computational thermal stresses and thermal stresses measured on a built-up structure. Element suitability, element density, and computational temperature discrepancies were studied to determine their impact on measured and calculated thermal stress. The optimum number of elements is established from a balance between element density and suitable safety margins, such that the answer is acceptably safe yet is economical from a computational viewpoint. It is noted that situations exist where relatively small excursions of calculated temperatures from measured values result in far more than proportional increases in thermal stress values. Measured residual stresses due to creep significantly exceeded the values computed by the piecewise linear elastic strain analogy approach. The most important element in the computation is the correct definition of the creep law. Computational methodology advances in predicting residual stresses due to creep require significantly more viscoelastic material characterization.
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    Subject Category: 39
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    Report Date: November 1987
    No. Pages: 27
    Keywords:      Comparison; Creep properties; Predictions; Structures; Temperature measurement; Thermal stresses; Titanium


  11. INELASTIC STRAIN ANALOGY FOR PIECEWISE LINEAR COMPUTATION OF CREEP RESIDUES IN BUILT-UP STRUCTURES , Technical Memorandum
    Authors: Jerald M. Jenkins
    Report Number: NASA-TM-86813
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An analogy between inelastic strains caused by temperature and those caused by creep is presented in terms of isotropic elasticity. It is shown how the theoretical aspects can be blended with existing finite-element computer programs to exact a piecewise linear solution. The creep effect is determined by using the thermal stress computational approach, if appropriate alterations are made to the thermal expansion of the individual elements. The overall transient solution is achieved by consecutive piecewise linear iterations. The total residue caused by creep is obtained by accumulating creep residues for each iteration and then resubmitting the total residues for each element as an equivalent input. A typical creep law is tested for incremental time convergence. The results indicate that the approach is practical, with a valid indication of the extent of creep after approximately 20 hr of incremental time. The general analogy between body forces and inelastic strain gradients is discussed with respect to how an inelastic problem can be worked as an elastic problem.
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    Subject Category: 39
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    Report Date: April 1987
    No. Pages: 13
    Keywords:      Computation; Creep analysis; Dynamic structural analysis; Inelastic stress; Linear systems; Residues


  12. AFTI/F-111 MAW FLIGHT CONTROL SYSTEM AND REDUNDANCY MANAGEMENT DESCRIPTION , Technical Memorandum
    Authors: Richard R. Larson
    Report Number: NASA-TM-88267
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The wing on the NASA F-111 transonic aircraft technology (TACT) airplane was modified to provide flexible leading and trailing edge flaps; this modified wing is known as the mission adaptive wing (MAW). A dual digital primary fly-by-wire flight control system was developed with analog backup reversion for redundancy. This report discusses the functions, design, and redundancy management of the flight control system for these flaps.
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    Subject Category: 05
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    Report Date: February 1987
    No. Pages: 72
    Keywords:      F-111 aircraft; Flaps (control surfaces); Flight control; Mission adaptive wings; Redundancy; Supersonic aircraft


  13. AIRCRAFT GROUND VIBRATION TESTING AT NASA AMES-DRYDEN FLIGHT RESEARCH FACILITY , Technical Memorandum
    Authors: Michael W. Kehoe
    Report Number: NASA-TM-88272
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: At the NASA Ames Research Center's Dryden Flight Research Facility at Edwards Air Force Base, California, a variety of ground vibration test techniques has been applied to an assortment of new or modified aerospace research vehicles. This paper presents a summary of these techniques and the experience gained from various applications. The role of ground vibration testing in the qualification of new and modified aircraft for flight is discussed. Data are presented for a wide variety of aircraft and component tests, including comparisons of sine-dwell, single-input random, and multiple-input random excitation methods on a JetStar airplane.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    Report Date: July 1987
    No. Pages: 21
    Keywords:      Certification; Ground tests; Qualifications; Research facilities; Vibration tests
    Notes: Presented at the 5th International Modal Analysis Conference, London, England, April 6-9, 1987


  14. THERMAL STRESS ANALYSIS OF SPACE SHUTTLE ORBITER WING SKIN PANEL AND THERMAL PROTECTION SYSTEM , Technical Memorandum
    Authors: William L. Ko (NASA Ames Research Center) and Jerald M. Jenkins (NASA Ames Research Center)
    Report Number: NASA-TM-88276
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Preflight thermal stress analysis of the space shuttle orbiter wing skin panel and the thermal protection system (TPS) was performed. The heated skin panel analyzed was rectangular in shape and contained a small square cool region at its center. The wing skin immediately outside the cool region was found to be close to the state of elastic instability in the chordwise direction based on the conservative temperature distribution. The wing skin was found to be quite stable in the spanwise direction. The potential wing skin thermal instability was not severe enough to tear apart the strain isolation pad (SIP) layer. Also, the preflight thermal stress analysis was performed on the TPS tile under the most severe temperature gradient during the simulated reentry heating. The tensile thermal stress induced in the TPS tile was found to be much lower than the tensile strength of the TPS material. The thermal bending of the TPS tile was not severe enough to cause tearing of the SIP layer.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 39
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    Report Date: March 1987
    No. Pages: 26
    Keywords:      Skin (structural member); Stress analysis; Thermal protection; Thermal stability; Thermal stresses; Wing panels


  15. COMPARISON OF FLIGHT-MEASURED AND CALCULATED TEMPERATURES ON THE SPACE SHUTTLE ORBITER , Technical Memorandum
    Authors: Leslie Gong, William L. Ko, Robert D. Quinn and W. Lance Richards
    Report Number: NASA-TM-88278
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Structural temperatures and thermal protection system surface temperatures were measured on the space shuttle during the flight of STS 5. The measured data are compared with values calculated at wing stations 134, 240, and 328 and at fuselage station 877. The theoretical temperatures were calculated using the structural performance and resizing finite element thermal analysis program. The comparisons show that the calculated temperatures are, generally, in good agreement with the measured data.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 34
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    Report Date: November 1987
    No. Pages: 74
    Keywords:      Flight tests; Space shuttle mission 31-A; Space shuttle orbiters; Surface temperature; Temperature measurement; Thermal analysis


  16. REAL-TIME COMPARISON OF X-29A FLIGHT DATA ANDSIMULATION DATA , Conference Report
    Authors: Joseph Gera (NASA Flight Research Center), Dominick Andrisani, II (Purdue University), Jeffrey E. Bauer (NASA Flight Research Center) and David B. Crawford (NASA Flight Research Center)
    Report Number: H-1387
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This paper presents a technique for comparing, in real time, the flight test time histories for X-29A aircraft with time histories computed from linearized mathematical models. Such a comparison allows the flight test personnel to verify that the aircraft is performing as predicted, to determine regions of nonlinear behavior, and to increase the rate of envelope expansion. The types of mathematical modeling and equipment required, the procedure used, and actual flight test results are discussed.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 08
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    Report Date: January 1987
    No. Pages: 12
    Keywords:      Aircraft stability; Flight simulation; Flight tests; Performance prediction; Real time operation; X-29 aircraft
    Notes: AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, January 12-15, 1987.


  17. THE PEST VERSION 2.1 USER'S MANUAL , Technical Memorandum
    Authors: James E. Murray and Richard E. Maine
    Report Number: NASA-TM-88280
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This report is a user's manual for version 2.1 of pEst, a FORTRAN 77 computer program for interactive parameter estimation in nonlinear dynamic systems. The pEst program allows the user complete generality in definig the nonlinear equations of motion used in the analysis. The equations of motion are specified by a set of FORTRAN subroutines; a set of routines for a general aircraft model is supplied with the program and is described in the report. The report also briefly discusses the scope of the parameter estimation problem the program addresses. The report gives detailed explanations of the purpose and usage of all available program commands and a description of the computational algorithms used in the program.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 61
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    Report Date: September 1987
    No. Pages: 75
    Keywords:      FORTRAN; Interactive control; Nonlinear systems; Parameter identification; User manuals (computer programs)


  18. AIRCRAFT PARAMETER ESTIMATION , Technical Memorandum
    Authors: Kenneth W. Iliff
    Report Number: NASA-TM-88281
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The aircraft parameter estimation problem is used to illustrate the utility of parameter estimation, which applies to many engineering and scientific fields. Maximum likelihood estimation has been used to extract stability and control derivatives from flight data for many years. This paper presents some of the basic concepts of aircraft parameter estimation and briefly surveys the literature in the field. The maximum likelihood estimator is discussed, and the basic concepts of minimization and estimation are examined for a simple simulated aircraft example. The cost functions that are to be minimized during estimation are defined and discussed. Graphic representations of the cost functions are given to illustrate the minimization process. Finally, the basic concepts are generalized, and estimation from flight data is discussed. Some of the major conclusions for the simulated example are also developed for the analysis of flight data from the F-14, highly maneuverable aircraft technology (HiMAT), and space shuttle vehicles.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    Report Date: January 1987
    No. Pages: 29
    Keywords:      Aircraft control; Aircraft stability; Flight tests; Maximum likelihood estimates; Parameterization
    Notes: Presented at the AIAA 25th Aerospace Sciences Meeting, Reno, Nevada, January 12-15, 1987.


  19. CHALLENGES IN MODELING THE X-29 FLIGHT TEST PERFORMANCE , Technical Memorandum
    Authors: John W. Hicks (NASA Ames Research Center), Jan Kania (Air Force Flight Test Center), Robert Pearce (Grumman Aerospace Corp.) and Glen Mills (NASA Ames Research Center)
    Report Number: NASA-TM-88282
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Presented are methods, instrumentation, and difficulties associated with drag measurement of the X-29A aircraft. The initial performance objective of the X-29A program emphasized drag polar shapes rather than absolute drag levels. Priorities during the flight envelope expansion restricted the evaluation of aircraft performance. Changes in aircraft configuration, uncertainties in angle-of-attack calibration, and limitations in instrumentation complicated the analysis. Limited engine instrumentation with uncertainties in overall in-flight thrust accuracy made it difficult to obtain reliable values of coefficient of parasite drag. The aircraft was incapable of tracking the automatic camber control trim schedule for optimum wing flaperon deflection during typical dynamic performance maneuvers; this has also complicated the drag polar shape modeling. The X-29A was far enough off the schedule that the developed trim drag correction procedure has proven inadequate. However, good drag polar shapes have been developed throughout the flight envelope. Preliminary flight results have compared well with wind tunnel predictions. A more comprehensive analysis must be done to complete performance models. The detailed flight performance program with a calibrated engine will benefit from the experience gained during this preliminary performance phase.
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    Subject Category: 05
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    Report Date: January 1987
    No. Pages: 14
    Keywords:      Aircraft performance; Drag measurement; Flight tests; Performance prediction; X-29 aircraft


  20. PREDICTED PITCHING MOMENT CHARACTERISTICS OF X-29A AIRCRAFT , Technical Memorandum
    Authors: Gerald D. Budd
    Report Number: NASA-TM-88284
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The predicted pitching moment characteristics of the X-29A aircraft are presented for angles of attack from 0 to 20 deg. and Mach numbers of 0.2, 0.6, 0.9, 1.2, and 1.5 for altitudes of sea level, 4572 m (15,000 ft), 9144 m (30,000 ft), and 12,192 m (40,000 ft). These data are for both rigid and flexible aircraft and for the full range of control-surface positions. The characteristics were extracted from a nonlinear, symmetric, flexibilized wind tunnel data base.
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    Subject Category: 02
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    Report Date: March 1987
    No. Pages: 67
    Keywords:      Angle of attack; Mach number; Pitching moments; Swept forward wings; X-29 aircraft


  21. HIGH ALTITUDE TURBULENCE FORSUPERSONIC CRUISE VEHICLES , Technical Memorandum
    Authors: L. J. Ehernberger
    Report Number: NASA-TM-88285
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The characterisitics of high altitude turbulence and its associated meteorological features are reviewed. Findings based on data from NASA flight research programs with prototype military aircraft, the XB-70 and YF-12A, are emphasized. An example of detailed numerical atmospheric simulations, which amy provide greatly increased understanding of these earlier turbulence observations, is presented. Comparisons between observation and numerical simulation should help to delineate the limitations of analysis techniques and improve our understanding of atmospheric processes in the stratosphere.
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    Subject Category: 47
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    Report Date: May 1987
    No. Pages: 18
    Keywords:      Atmospheric turbulence; Flight tests; High altitude; Stratosphere; Supersonic cruise aircraft research
    Notes: Presented at the 33rd Annual Meeting of the American Astronautical Society, Boulder, Colorado, October 26-29, 1986


  22. THERMAL STRESS ANALYSIS OF SPACE SHUTTLE ORBITER SUBJECTED TO REENTRY AERODYNAMIC HEATING , Technical Memorandum
    Authors: William L. Ko and Roger A. Fields
    Report Number: NASA-TM-88286
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A structural performance and resizing (SPAR) finite-element computer program and NASA structural analysis (NASTRAN) finite-element computer programs were used in the thermal stress analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. A SPAR structural model was set up for the entire left wing of the orbiter, and NASTRAN structural models were set up for: (1) a wing segment located at midspan of the orbiter left wing, and (2) a fuselage segment located at midfuselage. The thermal stress distributions in the orbiter structure were obtained and the critical high thermal stress regions were identified. It was found that the thermal stresses induced in the orbiter structure during reentry were relatively low. The thermal stress predictions from the whole wing model were considered to be more accurate than those from the wing segment model because the former accounts for temperature and stress effects throughout the entire wing.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 39
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    Report Date: October 1987
    No. Pages: 39
    Keywords:      Aerodynamic heating; Finite element method; Models; Reentry; Space shuttle orbiters; Thermal stresses


  23. FLIGHT TEST TECHNIQUES FOR THE X-29A AIRCRAFT , Technical Memorandum
    Authors: John W. Hicks, James M. Cooper, Jr. and Walter J. Sefic
    Report Number: NASA-TM-88289
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The X-29A advanced technology demonstrator is a single-seat, single-engine aircraft with a forward-swept wing. The aircraft incorporates many advanced technologies being considered for this country's next generation of aircraft. This unusual aircraft configuration, which had never been flown before, required a precise approach to flight envelope expansion. This paper describes the real-time analysis methods and flight test techniques used during the envelope expansion of the x-29A aircraft, including new and innovative approaches.
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    Subject Category: 05
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    Report Date: February 1987
    No. Pages: 13
    Keywords:      Aircraft stability; Flight envelope; Flight test instruments; X-29 aircraft; Data processing; Display devices; Dynamic structural analysis; In-flight monitoring; Real time operation; Structural strain
    Notes: Presented at the AIAA 25th Aerospace Sciences Meeting, Reno, Nevada, January 12-15, 1987


  24. FLUTTER CLEARANCE OF THE F-14 VARIABLE-SWEEP TRANSITION FLIGHT EXPERIMENT AIRPLANE, PHASE 1DOCUMENT ID: 19870018230 N (87N27663) FILE SERIES: NASA TECHNICAL R , Technical Memorandum
    Authors: Michael W. Kehoe
    Report Number: NASA-TM-88287
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An F-14 airplane was modified to become the test bed aircraft for the variable sweep transition flight experiment (VSTFE) program. The latter is a laminar flow program designed to measure the effects of wing sweep on boundary layer transition from laminar to turbulent flow. The airplane was modified by adding an upper surface foam-fiberglass glove over a portion of the left wing. Ground vibration and flight flutter testing were accomplished to clear a sufficient flight envelope to conduct the laminar flow experiments. Flight test data indicated satisfactory damping levels and damping trends for the elastic structural modes of the airplane. The data presented include frequency and damping as functions of Mach number.
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    Report Date: September 1987
    No. Pages: 68
    Keywords:      F-14 aircraft; Flutter analysis; Ground tests; Modal response; Research aircraft; Variable sweep wings; Vibration tests


  25. MANUAL FOR GETDATA VERSION 3.1: A FORTRAN UTILITY PROGRAM FOR TIME HISTORY DATA , Technical Memorandum
    Authors: Richard E. Maine
    Report Number: NASA-TM-88288
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This report documents version 3.1 of the GetData computer program. GetData is a utility program for manipulating files of time history data, i.e., data giving the values of parameters as functions of time. The most fundamental capability of GetData is extracting selected signals and time segments from an input file and writing the selected data to an output file. Other capabilities include converting file formats, merging data from several input files, time skewing, interpolating to common output times, and generating calculated output signals as functions of the input signals. This report also documents the interface standards for the subroutines used by GetData to read and write the time history files. All interface to the data files is through these subroutines, keeping the main body of GetData independent of the precise details of the file formats. Different file formats can be supported by changes restricted to these subroutines. Other computer programs conforming to the interface standards can call the same subroutines to read and write files in compatible formats.
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    Subject Category: 61
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    Report Date: October 1987
    No. Pages: 146
    Keywords:      Data processing; FORTRAN; User manuals (computer programs); File maintenence (computer programs; Interfaces; Subroutines; Time dependence


  26. IMPLEMENTATION OF A BLOCK LANCZOS ALGORITHM FOR EIGENPROBLEM SOLUTION OF GYROSCOPIC SYSTEMS , Technical Memorandum
    Authors: Kajal K. Gupta (NASA Ames Research Center) and Charles L. Lawson (Harvey Mudd Coll.)
    Report Number: NASA-TM-88290
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The details of implementation of a general numerical procedure developed for the accurate and economical computation of natural frequencies and associated modes of any elastic structure rotating along an arbitrary axis are described. A block version of the Lanczos algorithm is derived for the solution that fully exploits associated matrix sparsity and employs only real numbers in all relevant computations. It is also capable of determining multiple roots and proves to be most efficient when compared to other, similar, exisiting techniques.
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    Subject Category: 39
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    Report Date: April 1987
    No. Pages: 10
    Keywords:      Algorithms; Dynamic structural analysis; Eigenvalues; Finite element method; Spin stabilization; Vibration
    Notes: Prepared for presentation at the AIAA Dynamics Speciality Conference, Monterey, California, April 9, 1987.


  27. INTEGRATED AEROSERVOELASTIC ANALYSIS CAPABILITYWITH X-29A ANALYTICAL COMPARISONS , Conference Paper
    Authors: K. K. Gupta, M. J. Brenner and L. S. Voelker
    Report Number: H-1406
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An extension of the program STARS (a general-purpose structural analysis program) has been developed; this extension implements a complete aeroservoelastic analysis capability. Previous capabilities included finite-element modeling as well as statics, buckling, vibration, dynamic response, and flutter analyses. This paper presents a description and the formulation of STARS in its current state along with example dynamic, aeroelastic, and aeroservoelastic analyses pertaining to the X-29A aircraft. These examples include vibration analysis results as well as flutter analysis results obtained by the conventional k method and the velocity root-contour solution. Finally, selected open- and closed-loop aeroservoelastic analysis results based on a hybrid formulation are compared to illustrate, using the calculated frequency responses, the interactions of structures, aerodynamics, and flight controls.
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    Report Date: January 1987
    No. Pages: 12
    Keywords:      Aeroelasticity; Aeroservoelasticity; Aircraft stability; Structural analysis; X-29 aircraft
    Notes: Structural Dynamics and Materials Conference, 28th, Monterey, California, April 6-8, 1987 and AIAA Dynamics Specialists Conference, Monterey, California, April 9-10, 1987, Technical Papers. Part 2B (A87-33654 14-39). New York, American Institute of Aeronautics and Astronautics, 1987, p. 636-647.


  28. EFFECT OF ELEMENT SIZE ON THE SOLUTION ACCURACIES OF FINITE-ELEMENT HEAT TRANSFER AND THERMAL STRESS ANALYSES OF SPACE SHUTTLE ORBITER , Technical Memorandum
    Authors: William L. Ko and Timothy Olona
    Report Number: NASA-TM-88292
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The effect of element size on the solution accuracies of finite-element heat transfer and thermal stress analyses of space shuttle orbiter was investigated. Several structural performance and resizing (SPAR) thermal models and NASA structural analysis (NASTRAN) structural models were set up for the orbiter wing midspan bay 3. The thermal model was found to be the one that determines the limit of finite-element fineness because of the limitation of computational core space required for the radiation view factor calculations. The thermal stresses were found to be extremely sensitive to a slight variation of structural temperature distributions. The minimum degree of element fineness required for the thermal model to yield reasonably accurate solutions was established. The radiation view factor computation time was found to be insignificant compared with the total computer time required for the SPAR transient heat transfer analysis.
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    Subject Category: 39
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    Report Date: August 1987
    No. Pages: 51
    Keywords:      Finite element method; Heat transfer; Space shuttles; Thermal analysis; Thermal stresses
    Notes: Presented at the 5th International Conference on Numerical Methods in Thermal Problems, Montreal, Quebec, June 24 - July 3, 1987.


  29. ACCURACIES OF SOUTHWELL AND FORCE/STIFFNESS METHODS IN THE PREDICTION OF BUCKLING STRENGTH OF HYPERSONIC AIRCRAFT WING TUBULAR PANELS , Technical Memorandum
    Authors: William L. Ko
    Report Number: NASA-TM-88295
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Accuracies of the Southwell method and the force/stiffness (F/S) method are examined when the methods were used in the prediction of buckling loads of hypersonic aircraft wing tubular panels, based on nondestructive buckling test data. Various factors affecting the accuracies of the two methods were discussed. Effects of load cutoff point in the nondestructive buckling tests on the accuracies of the two methods were discussed in great detail. For the tubular panels under pure compression, the F/S method was found to give more accurate buckling load predictions than the Southwell method, which excessively overpredicts the buckling load. It was found that the Southwell method required a higher load cutoff point, as compared with the F/S method. In using the F/S method for predicting the buckling load of tubular panels under pure compression, the load cutoff point of approximately 50 percent of the critical load could give reasonably accurate predictions.
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    Report Date: November 1987
    No. Pages: 28
    Keywords:      Buckling; Hypersonic aircraft; Pipes (tubes); Predictions; Wing panels


  30. PRELIMINARY FLIGHT RESULTS OF AN ADAPTIVE ENGINE CONTROL SYSTEM OF AN F-15 AIRPLANE , Conference Paper
    Authors: Lawrence P. Myers and Kevin R. Walsh
    Report Number: H-1418
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Results of the flight demonstration of the adaptive engine control system (ADECS), an integrated flight and propulsion control system, are reported. The ADECS system provides additional engine thrust by increasing engine pressure ratio (EPR) at intermediate and afterburning power, with the amount of EPR uptrim modulated in accordance with the maneuver requirements, flight conditions, and engine information. As a result of EPR uptrimming, engine thrust has increased by as much as 10.5 percent, rate of climb has increased by 10 percent, and the time to climb from 10,000 to 40,000 ft has been reduced by 12.5 percent. Increases in acceleration of 9.3 and 13 percent have been obtained at intermediate and maximum power, respectively. No engine anomalies have been detected for EPR increases up to 12 percent.
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    Subject Category: 07
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    Report Date: June 1987
    No. Pages: 12
    Keywords:      Adaptive control; Electronic control; Engine control; F-15 aircraft; Flight tests; Fuel control
    Notes: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, California, June 29-July 2, 1987.


  31. THE VALUE OF EARLY FLIGHT EVALUATION OF PROPULSION CONCEPTS USING THE NASA F-15 RESEARCH AIRPLANE , Technical Memorandum
    Authors: Frank W. Burcham, Jr. and Ronald J. Ray
    Report Number: NASA-TM-100408
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The value of early flight evaluation of propulsion and propulsion control concepts was demonstrated on the NASA F-15 airplane in programs such as highly integrated digital electronic control (HIDEC), the F100 engine model derivative (EMD), and digital electronic engine control (DEEC). (In each case, the value of flight demonstration was conclusively demonstrated). This paper described these programs, and discusses the results that were not expected, based on ground test or analytical prediction. The role of flight demonstration in facilitating transfer of technology from the laboratory to operational airplanes is discussed.
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    Report Date: September 1987
    No. Pages: 15
    Keywords:      Evaluation; F-15 aircraft; Flight tests; Propulsion system configurations; Research aircraft
    Notes: Presented at the AIAA/AHS/ASEE Aircraft Design, Systems and Operations Meeting, St. Louis, Missouri, September 13-16, 1987.


  32. ADVANCED FIGHTER TECHNOLOGY INTEGRATION (AFTI)/F-16 AUTOMATED MANEUVERING ATTACK SYSTEM FINAL FLIGHT TEST RESULTS , Conference Paper
    Authors: Donald J. Dowden (USAF, Flight Test Center) and Denis E. Bessette
    Report Number: H-1421
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The AFTI F-16 Automated Maneuvering Attack System has undergone developmental and demonstration flight testing over a total of 347.3 flying hours in 237 sorties. The emphasis of this phase of the flight test program was on the development of automated guidance and control systems for air-to-air and air-to-ground weapons delivery, using a digital flight control system, dual avionics multiplex buses, an advanced FLIR sensor with laser ranger, integrated flight/fire-control software, advanced cockpit display and controls, and modified core Multinational Stage Improvement Program avionics.
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    Report Date: June 1987
    No. Pages: 11
    Keywords:      Aircraft maneuvers; Attacking (assaulting); Fighter aircraft; Fire control; Flight tests
    Notes: SAE, Aerospace Vehicle Conference, Washington, DC, June 8-10, 1987.


  33. DYNAMIC STABILITY AND HANDLING QUALITIES TESTS ON A HIGHLY AUGMENTED,STATICALLY UNSTABLE AIRPLANE , Technical Memorandum
    Authors: Joseph Gera and John T. Bosworth
    Report Number: NASA-TM-88297
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Initial envelope clearance and subsequent flight testing of a new, fully augmented airplane with an extremely high degree of static instability can place unusual demands on the flight test approach. Previous flight test experience with these kinds of airplanes is very limited or nonexistent. The safe and efficient flight testing may be further complicated by a multiplicity of control effectors that may be present on this class of airplanes. This paper describes some novel flight test and analysis techniques in the flight dynamics and handling qualities area. These techniques were utilized during the initial flight envelope clearance of the X-29A aircraft and were largely responsible for the completion of the flight controls clearance program without any incidents or significant delays.
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    Report Date: August 1987
    No. Pages: 16
    Keywords:      Controllability; Flight characteristics; Flight envelopes; Flight tests; Static stability; X-29 aircraft
    Notes: Presented at the AIAA Guidance, Navigation and Control Conference, Monterey, California, August 17-19, 1987 and SFTE 18th Annual Symposium, Amsterdam, Netherlands, September 28 - October 2, 1987.


  34. ELECTRO-OPTICAL FLIGHT DEFLECTION MEASUREMENTSYSTEM , Conference Paper
    Authors: V. Michael DeAngelis and Robert Fodale (Grumman Aerospace Corp.)
    Report Number: H-1426
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: This paper describes an electrooptical flight-deflection measurement system (FDMS) developed for use on highly-maneuverable-aircraft-technology (HiMAT) RPV flight research program. The FDMS provides in-flight measurements of the aircraft structural deflections and magnetic-tape recordings for automated data processing. The capabilities and limitations, requirements for installation on an aircraft, analytical considerations, and typical flight data acquired from the HiMAT research program are examined. The flight data indicate that the background light is the major obstacle to acquiring high-quality data and that the relationship between the target displacement and the output of the FDMS is nonlinear; however, the nonlinear effects can be minimized with judicious planning of the installation of the FDMS on the aircraft. Excellent flight deflection data were obtained from both the HiMAT and X-29 A flight research program with very little data lost as a result of encounters with severe background light.
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    Report Date: January 1987
    No. Pages: 14
    Keywords:      Aeroelasticity; Aircraft structures; Deflection; Displacement measurement; Electro-optics; Flight tests
    Notes: Society of Flight Test Engineers, Annual Symposium, 18th, Amsterdam, Netherlands, Sept. 28-Oct. 2, 1987, Proceedings (A88-51450 22-05). Lancaster, CA, Society of Flight Test Engineers, 1987.


  35. PRELIMINARY FLIGHT ASSESSMENT OF THE X-29A ADVANCED TECHNOLOGY DEMONSTRATOR , Technical Memorandum
    Authors: John W. Hicks and Neil W. Matheny
    Report Number: NASA-TM-100407
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Several new technologies integrated on the X-29A advanced technology demonstrator are being evaluated for the next generation of fighter aircraft. Some of the most noteworthy ones are the forward-swept wing, digital fly-by-wire flight control system, close-coupled wing-canard configuration, aeroelastically tailored composite wing skins, three-surface pitch control configuration, and a highly unstable airframe. The expansion of the aircraft 1-g and maneuver flight envelopes was recently completed over a two-year period in 84 flights. Overall flight results confirmed the viability of the aircraft design, and good agreement with preflight predictions was obtained. The individual technologies' operational workability and performance were confirmed. This paper deals with the flight test results and the preliminary evaluation of the X-29A design and technologies. A summary of the primary technical findings in structural static loads, structural dynamic characteristics, flight control system characteristics, aerodynamic stability and control, and aerodynamic performance is presented.
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    Report Date: September 1987
    No. Pages: 15
    Keywords:      Flight characteristics; Flight tests; Swept forward wings; Technology assessment; X-29 aircraft
    Notes: Presented at the AIAA/AHS/ASEE Aircraft Design, Systems and Operations Meeting, St. Louis, Missour, September 13-16, 1987.


  36. X-29A FORWARD-SWEPT-WING FLIGHT RESEARCH PROGRAM STATUS , Technical Memorandum
    Authors: Gary A. Trippensee and David P. Lux
    Report Number: NASA-TM-100413
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The X-29A aircraft is a fascinating combination of integrated technologies incorporated into a unique research aircraft. The X-29A program is multiple agency program with management and other responsibilities divided among NASA, DARPA, the U.S. Air Force, and the Grumman Corporation. An overview of the recently completed X-29A flight research program, objectives achieved, and a discussion of its future is presented. Also discussed are the flight test approach expanding the envelope, typical flight maneuvers performed, X-29A program accomplishments, lessons learned for the Number One aircraft, and future plans with the Number Two aircraft. A schedule for both aircraft is presented. A description of the unique technologies incorporated into the X-29A aircraft is given, along with descriptions of the onboard instrumentation system. The X-29A aircraft research program has proven highly successful. Using high fly rates from a very reliable experimental aircraft, the program has consistently met or exceeded its design and research goals.
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    Report Date: November 1987
    No. Pages: 11
    Keywords:      Flight tests; Research Management; Swept forward wings; X-29 aircraft; Flight envelopes; Instrument packages; Maneuvers; Technology assessment
    Notes: Presented at the SAE International Pacific Air and Space Technology Conference, Melbourne, Australia, November 13-17, 1987.


  37. HIDEC F-15 ADAPTIVE ENGINE CONTROL SYSTEMFLIGHT TEST RESULTS , Conference Paper
    Authors: James W. Smolka
    Report Number: H-1433
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: NASA-Ames' Highly Integrated Digital Electronic Control (HIDEC) flight test program aims to develop fully integrated airframe, propulsion, and flight control systems. The HIDEC F-15 adaptive engine control system flight test program has demonstrated that significant performance improvements are obtainable through the retention of stall-free engine operation throughout the aircraft flight and maneuver envelopes. The greatest thrust increase was projected for the medium-to-high altitude flight regime at subsonic speed which is of such importance to air combat. Adaptive engine control systems such as the HIDEC F-15's can be used to upgrade the performance of existing aircraft without resort to expensive reengining programs.
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    Report Date: January 1987
    No. Pages: 24
    Keywords:      Adaptive control; Engine airframe integration; Engine control; F-15 aircraft; Flight tests
    Notes: 1987 report to the aerospace profession; Society of Experimental Test Pilots, Symposium, 31st, Beverly Hills, CA, Sept. 23-26, 1987, Proceedings (A88-51426 22-05). Lancaster, CA, Society of Experimental Test Pilots, 1987. 1987 report to the aerospace profession Beverly Hills, CA Sept. 23-26, 1987
 
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