Dryden Technical Report Server
From NTRS: Locate an electronic (PDF) copy of the document.
- HUMAN TRANSFER CHARACTERISTICS IN FLIGHT AND GROUND SIMULATION FOR A ROLL TRACKING TASK , Technical Note
Authors: F. D. Newell and H. J. Smith
Report Number: NASA-TN-D-5007
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Human transfer characteristics in flight and ground simulation for roll tracking task.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 54
Availability:
Format(s) on-line:
PDF (3,361 KBytes)
Report Date: February 1969
No. Pages: 79
Keywords: Control simulation; Flight simulators; Pilot performance; Roll; Transferring
- FLIGHT INVESTIGATION OF A FLUIDIC AUTOPILOT SYSTEM , Technical Note
Authors: S. W. Gee and W. P. Lock
Report Number: NASA-TN-D-5298
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight tests of fluidic flight control system for aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 04
Availability:
Format(s) on-line:
PDF (1,432 KBytes)
Report Date: July 1969
No. Pages: 32
Keywords: Aircraft control; Flight control; Flight tests; Fluidics; Aircraft stability; Attitude control; Control; Control equipment; Performance tests
- HEAT-TRANSFER MEASUREMENTS OBTAINED ON THE X-15 AIRPLANE INCLUDING CORRELATIONS WITHWIND-TUNNEL RESULTS , Technical Memorandum
Authors: Robert D. Quinn and Frank V. Olinger
Report Number: NASA-TM-X-1705
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Heat transfer measurements were obtained on the X-15 airplane from two flights under quasi-steady conditions at a freestream Mach number of 5.1 and an angle of attack of 2.0 degrees, and a freestream Mach number of 4.98 and an angle of attack of 16.3 degrees. These measurements were made at corresponding freestream Reynolds numbers of 2.45 x 10(exp 6) and 1.31 x 10(exp 6) per foot. Experimental heat transfer coefficients derived from temperatures obtained from 200 recording thermocouples on the skin of the airplane are tabulated. Correlations with wind tunnel results show that the wind tunnel data are in fair to good agreement with the flight data obtained on the wing, ventral tail, and vertical tail at low angles of attack but are generally in poor agreement with high angle of attack data and the low angle of attack fuselage data.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1969
No. Pages: 64
Keywords: Flight tests; Heat transfer coefficients; Hypersonic heat transfer; Hypersonic speed; Wind tunnel tests; X-15 aircraft
- WIND-TUNNEL FORCE AND PRESSURE TESTS OF ROCKET-ENGINE NOZZLE EXTENSIONS ON THE 0.0667-SCALE X-15-2 MODEL AT SUPERSONIC AND HYPERSONIC SPEEDS , Technical Memorandum
Authors: E. J. Montoya and J. Nugent
Report Number: NASA-TM-X-1759
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Wind tunnel force and pressure tests of rocket engine nozzle extensions on X-15-2 model at supersonic and hypersonic speeds.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (2,784 KBytes)
Report Date: March 1969
No. Pages: 65
Keywords: Exhaust nozzles; Pressure measurement; Rocket engines; Wind tunnel models; X-15 aircraft
- A COMPARISON OF NEWTON-RAPHSON AND OTHER METHODS FOR DETERMINING STABILITY DERIVATIVES FROMFLIGHT DATA. , Conference Paper
Authors: K. W. Iliff, B. G. Powers and L. W. Taylor, Jr.
Report Number: H-544
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Newton-Raphson technique development for determining stability derivatives from flight data, noting use of a priori wind tunnel information.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1969
No. Pages: 16
Keywords: Aircraft stability; Flight tests; Newton-Raphson method; Stability derivatives
Notes: AIAA Paper 69-315. Presented at the AIAA and FTSS Conference, Houston, Texas, March 10-12, 1969.
- OPERATIONAL EXPERIENCES AND CHARACTERISTICS OF THE M2-F2 LIFTING BODY FLIGHT CONTROL SYSTEM , Technical Memorandum
Authors: B. M. Kock and W. D. Painter
Report Number: NASA-TM-X-1809
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: M2-F2 lifting body flight control system.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
Format(s) on-line:
PDF (1,471 KBytes)
Report Date: June 1969
No. Pages: 32
Keywords: Flight control; Lifting bodies; M-2F2 lifting body; Aerodynamic stability; Control surfaces; Supersonic flow
- EXPERIENCE USING BALAKRISHNAN'S EPSILON TECHNIQUE TO COMPUTE OPTIMUM FLIGHT PROFILES , Conference Paper
Authors: K. W. Iliff, H. J. Smith and L. W. Taylor, Jr.
Report Number: H-548
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Computing optimum flight profiles by Balakrishnan epsilon method, including equations of motion constraint in minimized cost function.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1969
No. Pages: 6
Keywords: Cost estimates; Equations of motion; Flight optimization; Flight paths; Digital techniques
Notes: AIAA Paper 69-75. Presented at the 7th AIAA Aerospace Sciences Meeting, New York, New York, January 20-22, 1969.
- VISUAL SIMULATION IMAGE GENERATION USING A FLYING-SPOT SCANNER , Technical Note
Authors: C. A. Wagner
Report Number: NASA-TN-D-5151
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Visual simulation image generation using flying spot scanner.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 09
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: April 1969
No. Pages: 58
Keywords: Flight simulation; Optical scanners; Television cameras; Visual signals
- FLIGHT MEASUREMENTS OF CANARD LOADS, CANARD BUFFETING, AND ELEVON AND WING TIP HINGE MOMENTS ON THE XB-70 AIRCRAFT INCLUDING COMPARISONS WITH PREDICTIONS , Technical Note
Authors: V. M. DeAngelis, E. L. Friend, J. M. Jenkins and R. C. Monaghan
Report Number: NASA-TN-D-5359
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: XB-70 aircraft flight tests of canard configurations.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
Format(s) on-line:
PDF (1,549 KBytes)
Report Date: August 1969
No. Pages: 30
Keywords: B-70 aircraft; Canard configurations; Flight tests; Aerodynamic loads; Buffeting; Elevons; Predictions; Wing tips
- THE FLIGHT INVESTIGATION OF PRESSURE PHENOMENA IN THE AIR INTAKE OF AN F-111A AIRPLANE. , Conference Paper
Authors: D. R. Bellman and D. L. Hughes
Report Number: H-558
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Jet engine compressor stalls in-flight investigation up to Mach 2 on F-111A by pressure sensors, noting steady state distortion role.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 07
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: June 1969
No. Pages: 12
Keywords: Compressor efficiency; F-111 aircraft; In-flight monitoring; Jet engines; Pressure effects
Notes: AIAA Paper 69-488. Presented at the 5th AIAA Propulstion Joint Specialist Conference, U. S. Airforce Academy, Colorado Springs, Colorado, June 9-13, 1969.
- EVALUATION OF AN INDIRECT VIEWING SYSTEM FOR LIFTING-BODY TERMINAL-AREA NAVIGATION ANDLANDING TASKS , Technical Note
Authors: W. H. Dana, H. G. Gaidsick and R. C. McCracken
Report Number: NASA-TN-D-5299
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Indirect optical viewing system in F-104B for simulated lifting-body approach and landing tasks.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 35
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: July 1969
No. Pages: 29
Keywords: Air navigation; Control simulation; Landing aids; Lifting bodies; Optical measuring instruments; Periscopes; Pilot performance; Visual tasks
- EVALUATION OF AN INFRARED HEATING SIMULATION OF A MACH 4.63 FLIGHT ON AN X-15 HORIZONTAL STABILIZER , Technical Note
Authors: R. A. Fields and A. Vano
Report Number: NASA-TN-D-5403
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Infrared heating simulation of Mach 4.63 flight on X-15 horizontal stabilizer.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 77
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: September 1969
No. Pages: 35
Keywords: Flight simulation; Heat flux; Infrared radiation; Stabilizers (fluid dynamics); X-15 aircraft
- DESIGN, DEVELOPMENT, AND FLIGHT TEST EXPERIENCE WITH LIFTING BODY STABILITY AUGMENTATIONSYSTEMS. , Conference Paper
Authors: R. P. Kotfilia and W. D. Painter
Report Number: H-563
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Lifting body stability augmentation systems design, development, ground tests and flight data including frequency response, limit cycle and structural resonance.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1969
No. Pages: 13
Keywords: Feedback control; Flight tests; Ground tests; Lifting bodies; Stabilization; Systems engineering
Notes: AIAA Paper 69-887. Presented at the AIAA Guidance, Control and Flight Mechanicas Conference, Princeton, New Jersay, August 18-20, 1969.
- FLIGHT-MEASURED AERODYNAMIC DRAG OF TWO LARGE EXTERNAL TANKS ATTACHED TO THE X-15-2 AIRPLANE AT MACH NUMBERS OF 1.6 TO 2.3 , Technical Memorandum
Authors: D. F. Fisher
Report Number: NASA-TM-X-1895
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Aerodynamic drag of external fuel tanks attached to X-15-2 airplane at Mach numbers of 1.6 to 2.3.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (823 KBytes)
Report Date: October 1969
No. Pages: 16
Keywords: Aerodynamic drag; External stores; X-15 aircraft; Aerodynamic coefficients; Ejection; Fuel tanks; Mach number
- A SIMPLE TECHNIQUE FOR AUTOMATIC COMPUTER EDITING OF BIODATA , Technical Note
Authors: C. E. Lewis, Jr., R. Swaroop and K. A. West
Report Number: NASA-TN-D-5275
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Statistical method for automatic computer editing of biological data.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 59
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: July 1969
No. Pages: 20
Keywords: Bioassay; Computer programs; Data reduction; Editing routines (computers)
- NASA HIGH TEMPERATURE LOADS CALIBRATION LABORATORY , Technical Memorandum
Authors: K. F. Anderson and W. J. Sefic
Report Number: NASA-TM-X-1868
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Design and operation of high temperature loads calibration laboratory.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 09
Availability:
Format(s) on-line:
PDF (1,095 KBytes)
Report Date: September 1969
No. Pages: 13
Keywords: Calibrating; Laboratories; Operations research; Strain gages; Aerodynamic heating; Aerodynamic loads
- FLIGHT-MEASURED HEAT TRANSFER AND SKIN FRICTION AT A MACH NUMBER OF 5.25 AND AT LOW WALL TEMPERATURES , Technical Memorandum
Authors: Robert D. Quinn and Frank V. Olinger
Report Number: NASA-TM-X-1921
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Turbulent skin friction and heat transfer coefficients were measured simultaneously on a test panel installed on the sharp leading edge upper vertical tail of the X-15 airplane at wall to recovery temperature ratios of 0.218 to 0.333 and at a nominal free stream Reynolds number of 1.54 x 10(exp 6) per foot. The data were obtained from one flight at a nominal free stream Mach number of 5.25. Reynolds analogy factors were derived from skin friction and heat transfer measurements. The measured data are compared with values predicted by various theories.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,355 KBytes)
Report Date: November 1969
No. Pages: 30
Keywords: Flight tests; Free flow; Heat transfer coefficients; Hypersonic heat transfer; Hypersonic speed; Skin friction; turbulence; X-15 aircraft
- FIN LOADS AND CONTROL-SURFACE HINGE MOMENTS MEASURED IN FULL-SCALE WIND-TUNNEL TESTS ON THE X-24A FLIGHT VEHICLE , Technical Memorandum
Authors: V. M. DeAngelis and M. H. Tang
Report Number: NASA-TM-X-1922
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Fin loads and control surface hinge moments measured in full scale wind tunnel tests on X-24A flight vehicle.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,470 KBytes)
Report Date: November 1969
No. Pages: 36
Keywords: Aerodynamic loads; Control surfaces; Lifting bodies; Wind tunnel stability tests; X-24 aircraft
- A NEW MODEL PERFORMANCE INDEX FOR THE ENGINEERING DESIGN OF FLIGHT CONTROL SYSTEMS. , Conference Paper
Authors: H. A. Rediess and H. P. Whitaker
Report Number: H-582
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Model performance index /PI/ providing criterion for approximating one dynamic flight control system by another based on geometrical representation of linear autonomous systems.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 04
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1969
No. Pages: 12
Keywords: Dynamic control; Flight control; Linear systems; Mathematical models; Systems engineering
Notes: AIAA Paper 69-885. Presented at the AIAA Guidance, Control and Flight Mechanics Conference, Princeton, New Jersey, August 18-20, 1969.
- LIFTING BODY FLIGHT TESTS AND ANALYSIS , Conference Paper
Authors: G. P. Layton, Jr. and J. G. McTigue
Report Number: H-583
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Reusable lifting entry vehicle flight tests, investigating handling qualities and subsonic- transonic aerodynamics of M2-F2 /M2-F3/, HL-10 and X-24A.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: October 1969
No. Pages: 8
Keywords: Aerodynamic characteristics; Controllability; Flight tests; Lifting reentry vehicles; Reusable spacecraft
Notes: SAE Paper 69-0662. Presented at the Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting, Los Angeles, California, October 6-10, 1969.
- VARIATION IN ENGINE NOISE FOR TWO LANDING-APPROACH CONFIGURATIONS OF A JET TRANSPORT AIRCRAFT , Technical Memorandum
Authors: E. J. Adkins, P. L. Lasagna and N. J. McLeod
Report Number: NASA-TM-X-1896
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Variation in engine noise for two landing approach configurations of jet transport aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
Format(s) on-line:
PDF (790 KBytes)
Report Date: October 1969
No. Pages: 15
Keywords: Engine noise; Jet aircraft; Transport aircraft; Approach; Flaps (control surfaces); Landing
- A COMPARISON OF MINIMUM TIME PROFILES FOR THE F-104 USING BALAKHRISHNAN'S EPSILON TECHNIQUEAND THE ENERGY METHOD , Conference Paper
Authors: K. W. Iliff, H. J. Smith and L. W. Taylor, Jr.
Report Number: H-600
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Minimum time profiles for F-104 aircraft by Balakrishnan epsilon technique, comparing solutions with energy method.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1969
No. Pages: 9
Keywords: F-104 aircraft; Flight time; Time optimal control; Computer programs; Control theory; Convergence; Energy methods; Equations of motion; Interative solution; Optimization
Notes: Presented at the Symposium on Optimization, Nice, France, June 29-July 5, 1969.
- FIXED-BASE SIMULATOR PILOT RATING SURVEYS FOR PREDICTING LATERAL-DIRECTIONAL HANDLING QUALITIES AND PILOT RATING VARIABILITY , Technical Note
Authors: K. W. Iliff and L. W. Taylor, Jr.
Report Number: NASA-TN-D-5358
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Pilot ratings of lateral directional handling for wide range of aircraft characteristics - graphs.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
Format(s) on-line:
PDF (2,476 KBytes)
Report Date: August 1969
No. Pages: 115
Keywords: Aircraft control; Graphs (charts); Lateral control; Pilots (personnel); Surveys; Variability
|
