Dryden Technical Report Server
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- FLIGHT-DETERMINED AERODYNAMIC STABILITY AND CONTROL DERIVATIVES OF THE M2-F2 LIFTING BODY VEHICLE AT SUBSONIC SPEEDS , Technical Memorandum
Authors: R. W. Kempel and R. C. Thompson
Report Number: NASA-TM-X-2413
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Aerodynamic derivatives were obtained for the M2-F2 lifting body flight vehicle in the subsonic flight region between Mach numbers of 0.41 and 0.64 and altitudes of 7000 feet to 45,000 feet. The derivatives were determined by a flight time history curve-fitting process utilizing a hybrid computer. The flight-determined derivatives are compared with wind-tunnel and predicted values. Modal-response characteristics, calculated from the flight derivatives, are presented.
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Subject Category: 02
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Report Date: December 1971
No. Pages: 35
Keywords: Aircraft control; Flight tests; M-2F2 lifting body; Stability derivatives; Subsonic speed; Aerodynamic characteristics; Computer programs; Data acquisition; Data reduction
- VERIFICATION OF TAKEOFF PERFORMANCE PREDICTIONS FOR THE XB-70 AIRPLANE , Technical Memorandum
Authors: T. J. Larson and W. G. Schweikhard
Report Number: NASA-TM-X-2215
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Takeoff performance predictions for XB-70 delta wing supersonic aircraft.
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Subject Category: 01
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Report Date: March 1971
No. Pages: 30
Keywords: Performance prediction; Supersonic aircraft; Takeoff runs; Aerodynamic drag; Aircraft performance; B-70 aircract; Delta wings
- VALIDATION OF A GENERAL PURPOSE AIRBORNE SIMULATOR FOR SIMULATION OF LARGE TRANSPORT AIRCRAFT HANDLING QUALITIES , Technical Note
Authors: K. J. Szalai
Report Number: NASA-TN-D-6431
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Analysis and validation of characteristics of general purpose airborne simulator for simulation of aerodynamic characteristics of large transport aircraft.
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Subject Category: 09
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Report Date: October 1971
No. Pages: 74
Keywords: Flight simulators; Test facilities; Transport aircraft; Aerodynamic characteristics; Aircraft control; Aircraft performance; Aircraft stability
- ENGINE EXHAUST NOISE DURING GROUND OPERATION OF THE XB-70 AIRPLANE , Technical Note
Authors: P. L. Lasagna and T. W. Putnam
Report Number: NASA-TN-D-7043
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measurement of engine exhaust noise during ground operation of XB-70 aircraft.
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Subject Category: 01
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Report Date: January 1971
No. Pages: 36
Keywords: Acoustic measurement; B-70 aircraft; Engine noise; Exhaust systems; Jet engines; Noise intensity
- COMPARISON OF WIND TUNNEL AND FLIGHT-MEASURED BASE PRESSURES FROM THE SHARP-LEADING-EDGE UPPER VERTICAL FIN OF THE X-15 AIRPLANE FOR TURBULENT FLOW AT MACH NUMBERS FROM 1.5 TO 5.0 , Technical Note
Authors: S. A. Goecke
Report Number: NASA-TN-D-6348
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight-measured base pressures from sharp leading edge upper vertical fin of X-15 aircraft compared with wind tunnel data for turbulent flow at Mach numbers from 1.5 to 5.0.
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Subject Category: 34
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Report Date: May 1971
No. Pages: 40
Keywords: Base pressure; Flight tests; Sharp leading edges; Turbulent flow; X-15 aircraft
- FLIGHT EVALUATION OF ANGLE OF ATTACK AS A CONTROL PARAMETER IN GENERAL-AVIATION AIRCRAFT , Technical Note
Authors: S. W. Gee, H. G. Gaidsick and E. K. Envoldson
Report Number: NASA-TN-D-6210
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Investigation of angle of attack information display for pilots to increase efficiency of general aviation aircraft operation.
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Subject Category: 01
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Report Date: March 1971
No. Pages: 24
Keywords: Angle of attack; Display devices; General aviation aircraft; Pilot performance; Aircraft performance; Flight control; Human factors engineering
- EXPERIENCE WITH THE X-15 ADAPTIVE FLIGHT CONTROL SYSTEM , Technical Note
Authors: Anonymous
Report Number: NASA-TN-D-6208
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight tests to determine reliability of X-15 self adaptive flight control system.
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Subject Category: 01
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Report Date: March 1971
No. Pages: 29
Keywords: Flight control; Flight tests; Self adaptive control systems; X-15 aircraft; Control stability; Controllability; Reliability engineering; Systems analysis
- INSTRUMENTATION AND DROP-TESTING TECHNIQUES FOR INVESTIGATING FLIGHT VEHICLES AND PERSONNEL PROTECTIVE SYSTEMS , Technical Memorandum
Authors: R. Carpenter, M. O. Thompson and J. H. Bowers
Report Number: NASA-TM-X-2149
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Instrumentation and drop testing techniques for investigating flight vehicle and personnel protective systems.
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Subject Category: 35
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Report Date: January 1971
No. Pages: 20
Keywords: Drop tests; Impact tests; Safety devices; Human factors engineering; Life support systems; Test facilities
- EVALUATION OF EFFECTS OF HIGH-ALTITUDE TURBULENCE ENCOUNTERS ON THE XB-70 AIRPLANE , Technical Note
Authors: R. R. Larson, B. J. Love and R J. Wilson
Report Number: NASA-TN-D-6457
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Evaluating effects of high altitude turbulence encounters on XB-70 airplane.
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Subject Category: 01
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Report Date: July 1971
No. Pages: 86
Keywords: Atmospheric turbulence; B-70 aircraft; Dynamic structural analysis; High altitude
- ANALYSIS OF A COUPLED ROLL SPIRAL MODE, PILOT INDUCED OSCILLATION EXPERIENCED WITH THE M2-F2 LIFTING BODY , Technical Note
Authors: R. W. Kempel
Report Number: NASA-TN-D-6496
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Analysis of coupled roll-spiral-mode, pilot induced oscillation occurring with M-2F2 lifting body.
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Subject Category: 02
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Report Date: September 1971
No. Pages: 59
Keywords: Aircraft performance; Aircraft stability; M-2F2 lifting body; Pilot induced oscillation; Aircraft landing; Angle of attack; Stability derivatives; Stable oscillations
- FLIGHT DETERMINED ACCELERATION AND CLIMB PERFORMANCE OF AN F-104G AIRPLANE FORUSE IN AN OPTIMUM FLIGHT PATH COMPUTER PROGRAM , Technical Note
Authors: R. T. Marshall
Report Number: NASA-TN-D-6398
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Computer program for optimum flight path defined by flight test investigation of performance characteristics /excess thrust, fuel flow, and climb potential/ of F-104G aircraft.
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Subject Category: 01
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Report Date: June 1971
No. Pages: 38
Keywords: Aircraft performance; Computer programs; F-104 aircraft; Mathematical models; Trajectory optimiation
- IN-FLIGHT USE OF TRAVERSING BOUNDARY-LAYER PROBES , Technical Note
Authors: E. J. Saltzman
Report Number: NASA-TN-D-6428
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: In-flight use of traversing boundary layer pitot probes with mechanical and electrical features and sample boundary layer profiles.
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Subject Category: 02
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Report Date: July 1971
No. Pages: 32
Keywords: Boundary layer flow; Flight tests; Pitot tubes; Test equipment; Coefficient of friction; Free flow; Probes; Velocity measurement; X-15 aircraft
- IN-FLIGHT EVALUATION OF THE LATERAL HANDLING OF A FOUR-ENGINE JET TRANSPORT DURING APPROACH AND LANDING , Technical Note
Authors: G. B. Gilyard and E. C. Holleman
Report Number: NASA-TN-D-6339
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight evaluation of lateral handling, stability, control, and flying qualities of jet transport aircraft during up-and-away and approach flight in landing configuration.
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Subject Category: 01
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Report Date: May 1971
No. Pages: 33
Keywords: Aerodynamic characteristics; Jet aircraft; Transport aircraft; Aircraft configurations; Aircraft control; Aircraft performance; Aircraft stability; Flight tests
- AN INVESTIGATION OF TWO VARIATIONS OF THE GAS GENERATOR METHOD TO CALCULATE THE THRUSTOF THE AFTERBURNING TURBOFAN ENGINES INSTALLED IN AN F-111A AIRPLANE , Technical Note
Authors: F. W. Burcham, Jr.
Report Number: NASA-TN-D-6297
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Two variations of gas generator method to calculate thrust of afterburning turbofan engines installed in F-111A aircraft.
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Subject Category: 07
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Report Date: April 1971
No. Pages: 31
Keywords: Afterburning; F-111 aircraft; Gas generators; Thrust measurement; Turbofan engines
- MOTION CUE AND SIMULATION FIDELITY ASPECTS OF THE VALIDATION OF A GENERAL PURPOSE AIRBORNE SIMULATOR , Technical Note
Authors: K. J. Szalai
Report Number: NASA-TN-D-6432
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Motion cue and simulation fidelity aspects of validation of general purpose airborne simulator.
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Subject Category: 09
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PDF (1,672 KBytes)
Report Date: October 1971
No. Pages: 37
Keywords: Flight simulators; Pilot performance; Space perception; B-70 aircraft; Performance tests; Physiological acceleration
- VERTICAL-FIN LOADS AND RUDDER HINGE-MOMENT MEASUREMENTS ON A 1/8 SCALE MODEL OF THE M2-F3 LIFTING BODY VEHICLE ATMACH NUMBERS FROM 0.50 TO 1.30 , Technical Memorandum
Authors: M. H. Tang
Report Number: NASA-TM-X-2286
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Transonic wind tunnel tests of vertical fin loads and rudder hinge moments on M2-F3 lifting body scale model at Mach 0.50 to 1.30.
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Subject Category: 02
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PDF (978 KBytes)
Report Date: May 1971
No. Pages: 44
Keywords: Aerial rudders; Aerodynamic loads; M-2F3 lifting body; Wind tunnel stability tests
- DIGITAL AUTOMATIC DATA REDUCTION TECHNIQUES USED IN A 1000-FLIGHT BIOMEDICAL STUDY , Technical Note
Authors: R. Carpenter and J. Roman
Report Number: NASA-TN-D-6601
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Techniques developed to automatically process a large quantity of physiological data obtained during a 1000-flight study are described. To reduce this data reliably, a study program was conducted using physiological data from X-15 flights as a data source for experimenting with signal enhancement and noise elimination techniques. The techniques include an automatic means for counting heart rates, averaging electrocardiogram waveforms, plotting histograms of heart rate versus frequency, and counting respiration rates. These techniques were used to reduce more than 2000 hours of physiological data recorded in flight.
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Subject Category: 52
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Report Date: December 1971
No. Pages: 17
Keywords: Bioinsturmentation; Data reduction; Digital techniques; Flight crews; Analog to digital converters; Automatic theory; Computer programming; Physiological responses; Signal to noise ratios; X-15 aircraft
- COMPARISONS OF IN-FLIGHT F-111A INLET PERFORMANCE FOR ON AND OFF SCHEDULED INLETGEOMETRY AT MACH NUMBERS OF 0.68 TO 2.18 , Technical Note
Authors: D. L. Hughes and R. A. Martin
Report Number: NASA-TN-D-6490
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.
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Subject Category: 01
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Report Date: September 1971
No. Pages: 47
Keywords: Automatic control; F-111 aircraft; Supersonic inlets; Transonic flight; Boundary layer separation; Compressor efficiency; Inlet flow; Pressure recovery
- A STATISTICAL TECHNIQUE FOR COMPUTER IDENTIFICATION OF OUTLIERS IN MULTIVARIATE DATA , Technical Note
Authors: R. Swaroop and W. R. Winter
Report Number: NASA-TN-D-6472
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Computer editing routine for data abnormalities in multivariate statistical analysis.
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Subject Category: 62
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Report Date: August 1971
No. Pages: 31
Keywords: Abnormalities; Computer programs; Editing routines (computers); Multivariate statisical analysis
- BOUNDARY LAYER TRANSITION DETECTION ON THE X-15 VERTICAL FIN USING SURFACE-PRESSURE-FLUCTUATION MEASUREMENTS , Technical Memorandum
Authors: T. L. Lewis and R. D. Banner
Report Number: NASA-TM-X-2466
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flush-mounted microphone on the vertical fin of an X-15 airplane was used to investigate boundary layer transition phenomenon during flights to peak altitudes of approximately 70,000 meters. The flight results were compared with those from wind tunnel studies, skin temperature measurements, and empirical prediction data. The Reynolds numbers determined for the end of transition were consistent with those obtained from wind tunnel studies. Maximum surface-pressure-fluctuation coefficients in the transition region were about an order of magnitude greater than those for fully developed turbulent flow. This was also consistent with wind tunnel data. It was also noted that the power-spectral-density estimates of the surface-pressure fluctuations were characterized by a shift in power from high frequencies to low frequencies as the boundary layer changed from turbulent to laminar flow. Large changes in power at the lowest frequencies appeared to mark
the beginning of transition.
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Subject Category: 01
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Report Date: December 1971
No. Pages: 18
Keywords: Boundary layer transition; Finned bodies; Pressure measurement; X-15 aircraft; Flight tests; Laminar flow; Power spectra; Reynolds number; Turbulent flow; Wind tunnels
- FLIGHT-MEASURED HL-10 LIFTING BODY CENTER FIN LOADS AND CONTROL SURFACE HINGE MOMENTS AND CORRELATION WITH WIND-TUNNEL PREDICTIONS , Technical Memorandum
Authors: M. H. Tang and G. P. E. Pearson
Report Number: NASA-TM-X-2419
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Aerodynamic characteristics of HL-10 lifting body and aerodynamic loads on center fin and control surfaces at subsonic, transonic, and supersonic speeds.
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Subject Category: 15
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Report Date: October 1971
No. Pages: 40
Keywords: Aerodynamic characteristics; Aerodynamic loads; HL-10 reentry vehicle; Aerodynamic configurations; Control surfaces; Wind tunnel stability tests
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