Dryden Technical Report Server
From NTRS: Locate an electronic (PDF) copy of the document.
- SUMMARY OF FLIGHT TESTS TO DETERMINE THE SPIN AND CONTROLLABILITY CHARACTERISTICS OF A REMOTELY PILOTED, LARGE-SCALE (3/8) FIGHTER AIRPLANE MODEL , Technical Note
Authors: E. C. Holleman
Report Number: NASA-TN-D-8052
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An unpowered, large, dynamically scaled airplane model was test flown by remote pilot to investigate the stability and controllability of the configuration at high angles of attack. The configuration proved to be departure/spin resistant; however, spins were obtained by using techniques developed on a flight support simulator. Spin modes at high and medium high angles of attack were identified, and recovery techniques were investigated. A flight support simulation of the airplane model mechanized with low speed wind tunnel data over an angle of attack range of + or - 90 deg. and an angle of sideslip range of + or - 40 deg. provided insight into the effects of altitude, stability, aerodynamic damping, and the operation of the augmented flight control system on spins. Aerodynamic derivatives determined from flight maneuvers were used to correlate model controllability with two proposed departure/spin design criteria.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 08
Availability:
Format(s) on-line:
PDF (4,137 KBytes)
Report Date: January 1976
No. Pages: 127
Keywords: Aircraft models; Controllability; Flight tests; Remotely piloted vehicles; Angle of attack; Fighter aircraft; Flight simulation; Spin stabilization
- AERODYNAMIC CHARACTERISTICS OF A VANE FLOW ANGULARITY SENSOR SYSTEM CAPABLE OF MEASURING FLIGHTPATH ACCELERATIONS FOR THE MACH NUMBER RANGE FROM 0.40 TO 2.54 , Technical Note
Authors: G. M. Sakamoto
Report Number: NASA-TN-D-8242
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The aerodynamic characteristics of the angle of attack vane and the angle of sideslip vane are summarized. The test conditions ranged in free stream Mach number from 0.40 to 2.54, in angle of attack from -2 deg to 22 deg, in angle of sideslip from -2 deg to 12 deg, and in Reynolds number from 590,000 per meter to 1.8 million per meter. The results of the wind tunnel investigation are compared with results obtained with similar vane configurations. Comparisons with a NACA vane configuration are also made. In addition, wind tunnel-derived upwash for the test installation is compared with analytical predictions.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 06
Availability:
Format(s) on-line:
PDF (1,694 KBytes)
Report Date: May 1976
No. Pages: 45
Keywords: Aerodynamic characteristics; Wind tunnel tests; Wind vanes; Angle of attack; Flight paths; Flow direction indicators; Flow velocity; Mach numbers
- ADVANCED CONTROL TECHNOLOGY AND ITS POTENTIAL FOR FUTURE TRANSPORT AIRCRAFT , Technical Memorandum
Authors: Anonymous
Report Number: NASA-TM-X-3409
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The topics covered include fly by wire, digital control, control configured vehicles, applications to advanced flight vehicles, advanced propulsion control systems, and active control technology for transport aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1976
No. Pages: 1005
Notes: Presented at a Symposium on Adv. Control Technol., Los Angeles, July 9-11, 1974.
- SUBSONIC STABILITY AND CONTROL DERIVATIVES FOR AN UNPOWERED, REMOTELY PILOTED 3/8-SCALE F-15AIRPLANE MODEL OBTAINED FROM FLIGHT TEST , Technical Note
Authors: K. W. Iliff, R. E. Maine and M. F. Shafer
Report Number: NASA-TN-D-8136
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: In response to the interest in airplane configuration characteristics at high angles of attack, an unpowered remotely piloted 3/8-scale F-15 airplane model was flight tested. The subsonic stability and control characteristics of this airplane model over an angle of attack range of -20 to 53 deg are documented. The remotely piloted technique for obtaining flight test data was found to provide adequate stability and control derivatives. The remotely piloted technique provided an opportunity to test the aircraft mathematical model in an angle of attack regime not previously examined in flight test. The variation of most of the derivative estimates with angle of attack was found to be consistent, particularly when the data were supplemented by uncertainty levels.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 08
Availability:
Format(s) on-line:
PDF (1,542 KBytes)
Report Date: January 1976
No. Pages: 33
Keywords: F-15 aircraft; Remotely piloted vehicles; Stability derivatives; Aircraft models; Flight tests; Subsonic speed
- PRACTICAL ASPECTS OF A MAXIMUM LIKELIHOOD ESTIMATION METHOD TO EXTRACT STABILITY AND CONTROL DERIVATIVES FROM FLIGHT DATA , Technical Note
Authors: K. W. Iliff and R. E. Maine
Report Number: NASA-TN-D-8209
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A maximum likelihood estimation method was applied to flight data and procedures to facilitate the routine analysis of a large amount of flight data were described. Techniques that can be used to obtain stability and control derivatives from aircraft maneuvers that are less than ideal for this purpose are described. The techniques involve detecting and correcting the effects of dependent or nearly dependent variables, structural vibration, data drift, inadequate instrumentation, and difficulties with the data acquisition system and the mathematical model. The use of uncertainty levels and multiple maneuver analysis also proved to be useful in improving the quality of the estimated coefficients. The procedures used for editing the data and for overall analysis are also discussed.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 08
Availability:
Format(s) on-line:
PDF (1,677 KBytes)
Report Date: April 1976
No. Pages: 34
Keywords: Aircraft control; Data reduction; Flight tests; Maximum likelihood estimates; Stability derivatives
- AN EXACT TRANSFORMATION FROM GEOCENTRIC TO GEODETIC COORDINATES FOR NONZERO ALTITUDES , Technical Report
Authors: D. R. Hedgley, Jr.
Report Number: NASA-TR-R-458
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An exact method for the nonzero altitude transformation from geocentric to geodetic coordinates is derived. The method is mathematically general and should serve as a primary standard.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 61
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1976
No. Pages: 19
Keywords: Geocentric coordinates; Geodetic coordinates; Transformations (mathematics); Altitude; Standards
- EVALUATION OF AN ENVELOPE-LIMITING DEVICE USING SIMULATION AND FLIGHT TEST OF A REMOTELY PILOTEDRESEARCH VEHICLE , Technical Note
Authors: K. L. Petersen
Report Number: NASA-TN-D-8216
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The operating characteristics of a nonlinear envelope-limiting device were investigated at extreme flight conditions by using a real time digital aircraft spin simulation and flight tests of a scale model remotely piloted research vehicle. A digital mechanization of the F-15 control system, including the stall inhibiter, was used in the simulation and in the control system of the scale model. The operational characteristics of the stall inhibiter and the effects of the stall inhibiter on the spin susceptibility of the airplane were investigated.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 08
Availability:
Format(s) on-line:
PDF (738 KBytes)
Report Date: April 1976
No. Pages: 19
Keywords: Automatic flight control; Flight simulation; Remotely piloted vehicles; Aerodynamic stalling
- STATUS OF THE NASA YF-12 PROPULSION RESEARCH PROGRAM , Technical Memorandum
Authors: J. A. Albers
Report Number: NASA-TM-X-56039
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The YF-12 research program was initiated to establish a technology base for the design of an efficient propulsion system for supersonic cruise aircraft. The major technology areas under investigation in this program are inlet design analysis, propulsion system steady-state performance, propulsion system dynamic performance, inlet and engine control systems, and airframe/propulsion system interactions. The objectives, technical approach, and status of the YF-12 propulsion program are discussed. Also discussed are the results obtained to date by the NASA Ames, Lewis, and Dryden research centers. The expected technical results and proposed future programs are also given. Propulsion system configurations are shown.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 07
Availability:
Format(s) on-line:
PDF (1,374 KBytes)
Report Date: March 1976
No. Pages: 32
Keywords: Aircraft engines; Engine design; Propulsion system performance; Supersonic aircraft
- SEMIEMPIRICAL AIRFRAME NOISE PREDICTION MODEL AND EVALUATION WITH FLIGHT DATA , Technical Memorandum
Authors: A. S. Hersh, F. W. Burcham, Jr., T. W. Putnam and P. L. Lasagna
Report Number: NASA-TM-X-56041
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A semiempirical maximum overall sound pressure level (OASPL) airframe noise model was derived. Noise radiated from aircraft wings was modeled on the trailing edge diffractes quadrupole sound theory. The acoustic dipole sound theory was used to model noise from the landing gear. The model was correlated with maximum OASPL flyover noise measurements obtained for three jet aircraft. One third octave band sound pressure level flyover data was correlated and interpreted.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 71
Availability:
Format(s) on-line:
PDF (1,519 KBytes)
Report Date: December 1976
No. Pages: 36
Keywords: Aerodynamic noise; Airframes; Mathematical models; Performance prediction; Sound pressure
|
