Dryden Technical Report Server
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- A PRETENSIONING CONCEPT FOR RELIEF OF CRITICAL LEADING-EDGE THERMAL STRESS , Technical Note
Authors: J. M. Jenkins
Report Number: NASA-TN-D-3507
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper introduces an analytical concept designed to relieve problems arising from the chordwise temperature gradients by reducing the magnitude of critical compressive stress in a leading edge. The reduction is accomplished by adding an internal column that applies an internal load to the ends of the leading edge. Equations that define the behavior of a pretensioned leading edge are developed and applied to a mathematical model to demonstrate the mechanics of using the concept.
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Report Date: July 1966
No. Pages: 24
Keywords: Critical loading; High temperature; Leading edges; Stagnation point; Thermal stresses.
- EXPERIMENTAL INVESTIGATION OF THERMAL-BUCKLING CHARACTERISTICS OF FLANGED, THIN-SHELL LEADING EDGES , Technical Note
Authors: J. M. Jenkins and W. J. Sefic
Report Number: NASA-TN-D-3243
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Thermal buckling characteristics of flanged thin shell leading edges - aerodynamic heating.
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Report Date: January 1966
No. Pages: 31
Keywords: Aerodynamic heating; Leading edges; Thermal buckling; Thin walled shells.
- SUMMARY OF HIGH-ALTITUDE AND ENTRY FLIGHT CONTROL EXPERIENCE WITH THE X-15 AIRPLANE , Technical Note
Authors: E. C. Holleman
Report Number: NASA-TN-D-3386
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: High altitude performance and reentry flight control of X-15 aircraft.
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Report Date: April 1966
No. Pages: 68
Keywords: Aircraft control; Aircraft performance; Flight control; High altitude; X-15 aircraft.
- SUMMARY OF FULL-SCALE LIFT AND DRAG CHARACTERISTICS OF THE X-15 AIRPLANE , Technical Note
Authors: E. J. Saltzman and D. J. Garringer
Report Number: NASA-TN-D-3343
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Full-scale power-off flight lift and drag characteristics of X-15 aircraft.
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Report Date: March 1966
No. Pages: 49
Keywords: Aerodynamic drag; Drag; Drag coefficients; Flight characteristics; Lift drag ratio; Mach number.
- MEASURED AND CALCULATED FLOW CONDITIONS ON THE FORWARD FUSELAGE OF THE X-15 AIRPLANE AND MODEL AT MACH NUMBERS FROM 3.0 TO 8.0 , Technical Note
Authors: M. Palitz
Report Number: NASA-TN-D-3447
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Early analyses of X-15 flight heat-transfer data were based on calculated values of the local-flow conditions. The resultant differences between measured and predicted heat transfer were thought to be partially due to an incomplete knowledge of the local fluid properties. Subsequently, a flight investigation was made to determine the extent and character of the local flow on the X-15 airplane in order to aid in the interpretation of the measured heat-transfer data. The results of the flow-field investigation on the forebody of the X-15 are presented and analyzed in this paper.
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Report Date: June 1966
No. Pages: 46
Keywords: Aircraft models; Angle of attack; Fuselages; Hypersonic flow; Mach number.
- DRY ELECTRODES FOR PHYSIOLOGICAL MONITORING , Technical Note
Authors: C. W. Patten, F. B. Ramme and J. A. Roman
Report Number: NASA-TN-D-3414
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Subject preparation and application of sprayed dry electrodes for physiological monitoring.
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Subject Category: 52
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Report Date: May 1966
No. Pages: 40
Keywords: Bioinstrumentation; Drying; Electrocardiography; Electrodes; Electroencephalography.
- DRAG AND WEAR CHARACTERISTICS OF VARIOUS SKID MATERIALS ON DISSIMILAR LAKEBED SURFACES DURING THE SLIDEOUT OF THE X-15 AIRPLANE , Technical Note
Authors: R. J. Wilson
Report Number: NASA-TN-D-3331
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An investigation was made to determine the coefficients of friction and the wear characteristics for X-15 landing gear skids of various materials. Data are presented for skids made of 4130 steel, with and without cermet coating and Inconel X for several lakebed-surface conditions. The mean coefficient of friction on a dry-hard surface was found to be 0.30 for 4130 steel skids, 0.36 for 4130 steel skids with cermet coating, and 0.35 for Inconel X surface was 0.46; for Inconel skids on a damp surface the mean value was 0.25. Flight data are comparted with experimental ground-tow test data on natural and simulated lakebed surfaces. Also included is the variation of skid wear with slideout distance.
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Report Date: March 1966
No. Pages: 28
Keywords: Aircraft landing; Cermets; Coefficient of friction; Drag; Landing Gear.
- AN EVALUATION OF GENERAL AVIATION AIRCRAFT FLYING QUALITIES. , Conference Paper
Authors: Marvin R. Barber, Fred W. Haise and Charles K. Jones
Report Number: H-400
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flying qualities of six late-model personal-owner aircraft in visual and instrument flight.
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Report Date: March 1966
No. Pages: 12
Keywords: Aerodynamics; Aircraft design; Aircraft performance; Controllability; Flight characteristics.
Notes: AC/NASA, FLIGHT RESEARCH CENTER, EDWARDS AFB, CALIF./. SOCIETY OF AUTOMOTIVE ENGINEERS, BUSINESS AIRCRAFT CONFERENCE, WICHITA, KAN., MAR. 30- APR. 1, 1966, PAPER 660219.
- A PARAMETRIC STUDY OF FACTORS INFLUENCING THE DEEP-STALL PITCH-UP CHARACTERISTICS OF T-TAIL TRANSPORT AIRCRAFT , Technical Note
Authors: B. G. Powers
Report Number: NASA-TN-D-3370
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper presents the results of the program, in which the transport-type aircraft were investigated. A series of stall maneuvers was made with deceleration rates into the stall of 1, 3, and 5 knots per second, with recovery initiated over a range of angle attack. The relative effects of the shape of the pitching-moment curves in the deep-stall region as well as in the initial-stall region were determined in terms of angle-of-attack overshoot and altitude losses during recovery.
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Report Date: August 1966
No. Pages: 28
Keywords: Aerodynamic stalling; Analog computers; Computer programs; Pitching moments; T shape.
- A TECHNIQUE FOR MEASURING MESOSPHERIC DENSITIES WITH THE X-15 RESEARCH AIRPLANE , Conference Paper
Authors: Terry J. Larson and Alan Covington
Report Number: H-405
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Atmospheric-density measurements for altitudes between 30 kilometers and 74 kilometers were obtained during flights with the X-15 research airplane in the southwestern United States. The pilot-pressure method used to derive the densities is discussed in terms of its applicability to X-15 trajectory and instrumentation characteristics. The use of radar tracking to derive X-15 velocity and altitude is described, as well as the manner in which rawinsonde and rocketsonde data are applied. Flow-angularity effects were avoided by measuring stagnation pressures on a spherical flow-direction sensor, which maintains continuous alignment of the pilot-pressure port with the local flow vector. The quality of the data was further enhanced by applying semiempirical lag corrections to the pressure measurements. The measured density and derived temperature data from the X-15 agree well with rawinsonde data at low altitudes and with Arcas rocketsonde data at higher
altitudes.
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Subject Category: 46
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Report Date: June 1966
No. Pages: 16
Keywords: Airborne equipment; Altitude; Atmospheric density; Conferences; Density measurement.
Notes: AA/NASA, FLIGHT RESEARCH CENTER, EDWARDS, CALIF./. AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 4TH, LOS ANGELES, CALIF., JUN. 27-29, 1966, AIAA PAPER 66-441.
- DESIGN, DEVELOPMENT, AND UTILIZATION OF A GENERAL PURPOSE AIRBORNE SIMULATOR , Technical Memorandum
Authors: D. T. Berry and D. A. Deets
Report Number: NASA-TM-X-74543
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
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Subject Category: 09
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Report Date: May 1966
No. Pages: 22
Keywords: Aircraft control; Control stability; Design analysis; Flight simulators; Ground based control.
Notes: Presented at 28th AGARD Flight Mech. Panel, Paris, 10-11 May 1966.
- RECENT RESEARCH DIRECTED TOWARD THE PREDICTION OF LATERAL-DIRECTIONAL HANDLING QUALITIES , Technical Memorandum
Authors: L. W. Taylor, Jr. and K. W. Iliff
Report Number: NASA-TM-X-59621
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Lateral-directional handling qualities survey to develop technique for predicting pilot ratings.
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Report Date: May 1966
No. Pages: 22
Keywords: Controllability; Lateral control; Pilot performance; Predictions; Ratings.
Notes: PARIS, AGARD, MAY 1966 22 P REFS PRESENTED AT 28TH MEETING OF THE AGARD FLIGHT MECH. PANEL, 10-11 MAY 1966.
- ANALYSIS OF AN EMERGENCY DECELERATION AND DESCENT OF THE XB-70-1 AIRPLANE DUE TO ENGINE DAMAGE RESULTING FROM STRUCTURAL FAILURE , Technical Memorandum
Authors: C. H. Wolowicz
Report Number: NASA-TM-X-1195
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Analyzing emergency deceleration and descent of XB-70-1 airplane due to engine damage resulting from structural failure for supersonic transport data.
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Report Date: March 1966
No. Pages: 35
Keywords: Aircraft performance; Damage; Deceleration; Descent; Emergencies.
- SURVEY OF OPERATION AND COST EXPERIENCE OF THE X-15 AIRPLANE AS A REUSABLE SPACE VEHICLE , Technical Note
Authors: J. E. Love and W. R. Young
Report Number: NASA-TN-D-3732
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The X-15 airplane has been flown more than 150 times in an environment similar to that anticipated for many of the reusable space vehicles being studied. Data are presented on X-15 development and operational costs, turnaround time, and refurbishment cycles, based upon actual operation of the aircraft. For example, 27 flights were accomplished in 1964 at a total cost of $16,268,000, or an average cost of more than $602,000 per flight. It is believed that information from the X-15 program will be helpful in feasibility studies of the reusable-vehicle concept, inasmuch as the X-15 operation is more directly comparable than any other operational program to the reusable systems being considered.
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Subject Category: 15
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Report Date: November 1966
No. Pages: 12
Keywords: Cost estimates; Costs; Manpower; Reusable spacecraft; Surveys; X-15 aircraft.
- COMPARISON OF MEASURED AND CALCULATED TURBULENT HEAT TRANSFER ON THE X-15 AIRPLANE AT ANGLES OF ATTACK UP TO 19.0 DEG , Technical Memorandum
Authors: R. D. Quinn and M. Palitz
Report Number: NASA-TM-X-1291
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
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Report Date: September 1966
No. Pages: 56
Keywords: Aerodynamic characteristics; Aerodynamic coefficients; Aerothermodynamics; Turbulent flow; X-15 aircraft.
- CONTROL EXPERIENCES OF THE X-15 PERTINENT TO LIFTING ENTRY , Technical Note
Authors: E. C. Holleman
Report Number: NASA-TN-D-3262
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight control of X-25 aircraft at lifting entry- entry control system for altitudes up to 350,000 feet.
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Report Date: February 1966
No. Pages: 16
Keywords: Aircraft control; Altitude; Atmospheric entry; Flight control; High altitude.
- A SUMMARY OF X-15 HEAT TRANSFER AND SKIN FRICTION MEASUREMENTS , Technical Memorandum
Authors: R. D. Banner and A. E. Kuhl
Report Number: NASA-TM-X-1210
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measured local Mach numbers and heat transfer obtained on the lower surface of the X-15 wing and bottom centerline of the fuselage at angles of attack up to 18 degrees and on the vertical fin with both a sharp and a blunt leading edge are summarized and compared with calculations using Eckert's reference-temperature method. Direct measurements of skin friction on the surface of the sharp-leading-edge vertical fin are also presented. It is shown that both the heat-transfer and skin-friction data can be predicted by neglecting the effect of wall temperature in the calculation of the reference temperature by Eckert's method. Uncertainties in level and trend of Reynolds analogy factor with Mach number are discussed, and a planned flight investigation is described.
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Report Date: February 1966
No. Pages: 14
Keywords: Angle of attack; Heat transfer; Mach number; Skin friction; X-15 aircraft.
- FLIGHT MEASUREMENTS OF BOUNDARY-LAYER NOISE ON THE X-15 , Technical Note
Authors: T. L. Lewis and N. J. McLeod
Report Number: NASA-TN-D-3364
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Boundary layer noise measurements in X-15 aircraft flight.
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Report Date: March 1966
No. Pages: 15
Keywords: Aerodynamic noise; Boundary layers; Flight conditions; In-flight monitoring; Measuring instruments.
- A SUMMARY OF THE X-15 LANDING LOADS , Technical Note
Authors: J. M. McKay and R. B. Noll
Report Number: NASA-TN-D-3263
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Summary of X-15 aircraft landing loads.
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Report Date: February 1966
No. Pages: 13
Keywords: Aircraft landing; Landing loads; Touchdown; X-15 aircraft.
- FLIGHT RESEARCH PROGRAM. III - HIGH IMPEDANCE ELECTRODE TECHNIQUES , Journal Article
Authors: James Roman
Report Number: H-422
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper describes electrode techniques designed for large-scale flight physiological data collection on a routine basis. Large-scale data collection requires both smaller demands on crew time and less interference with crew comfort than could be achieved by former methods. The resistive components of electrode impedance appears to be related primarily to the extent of skin preparation. For any one method of skin preparation, both resistance and capacitance appear to be primarily a function of electrode area. Motion artifacts are not caused by changes in electrode impedance. Dry electrodes showing a resistive component in excess of 50,000 ohms can be used to obtain tracings of quality comparable, and in some cases superior to those obtained with larger wet electrodes.
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Subject Category: 52
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Report Date: August 1966
No. Pages: 6
Keywords: Biotelemetry; Data acquisition; Data recording; Electrical impedance; Electrodes.
Notes: AEROSPACE MEDICINE, VOL. 37, AUG. 1966, P. 790- 795.
- SUMMARY OF PRELIMINARY DATA DERIVED FROM THE XB-70 AIRPLANES , Technical Memorandum
Authors: W. H. Andrews
Report Number: NASA-TM-X-1240
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Preliminary data of handling, thermal response, propulsion system, noise, and sonic boom for XB-70.
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Report Date: June 1966
No. Pages: 41
Keywords: B-70 aircraft; Flight tests; Performance; Propulsion; Sonic booms; Supersonic transports.
- HUMAN DESCRIBING FUNCTIONS MEASURED IN FLIGHT AND ONSIMULATORS
Authors: Harriet J. Smith
Report Number: H-430
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Human describing functions measured in flight by T-33 variable-stability airplane, and by ground simulation of instrument flight of same aircraft and on analog computer with contact display.
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Report Date: January 1966
No. Pages: 12
Keywords: Analog computers; Analog simulation; Conferences; Human factors engineering; In-flight monitoring.
Notes: IN ITS MANUAL CONTROL 1966 P 279-290. SP-128.
- CONSIDERATIONS IN THE DETERMINATION OF STABILITY ANDCONTROL DERIVATIVES AND DYNAMIC CHARACTERISTICS FROM FLIGHTDATA
Authors: C. H. Wolowicz
Report Number: H-433
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This report is the handbook on the determination of stability and control characteristics from flight test. It describes several axis systems, axis transformations, the equations of motions and their limitations, techniques used to determine the mass characteristics of the airplane, the installation and behavior of flight instrumentation, flight test techniques, and the theory and limitations of techniques used to determine the stability and control characteristics from flight data. This report brings all the factors together in the determination of stability and control and provide a ready reference of pertinent information. It is a greatly expanded version of AGARD 224, Stability-Derivative Determination From Flight Data, by Chester H. Wolowicz and Euclid C. Holleman.
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Report Date: January 1966
No. Pages: 190
Keywords: Derivation; Dynamic characteristics; Flight tests; Stability.
Notes: AGARD Report 549, PT. I.
- OPERATIONAL EXPERIENCE WITH THE ELECTRONIC FLIGHT CONTROL SYSTEMS OF A LUNAR-LANDING RESEARCH VEHICLE , Technical Note
Authors: C. R. Jarvis
Report Number: NASA-TN-D-3689
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Two research vehicles were delivered to the NASA Flight Research Center in the Spring of 1964. After delivery, several months were devoted to checking systems and installing research instrumentation. During this period, many problems were encountered which required extensive modifications to the vehicle and its systems. Subsequent development flight testing disclosed additional problems and resulted in further modifications. This paper discusses the nature of these problems and the performance of the flight control systems during the early flights.
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Report Date: October 1966
No. Pages: 45
Keywords: Electronic control; Electronic equipment; Flight control; Lunar landing; Lunar landing modules.
- FLIGHT RESEARCH PROGRAM. V. MASS SPECTROMETER IN MEDICAL MONITORING , Journal Article
Authors: James Roman and Wayne H. Brigden
Report Number: H-440
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Mass spectrometers, traditionally large and complicated instruments, have been miniaturized and greatly simplified for the National Space Program. This recent development opens new areas to medicine and to space medicine in particular. The principles of operation of mass spectrometers will soon be important to those engaged in physiological research or in medical monitoring. They are discussed in this paper. A summary of flight test data obtained with a small mass spectrometer in a jet aircraft is presented.
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Subject Category: 52
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Report Date: December 1966
No. Pages: 5
Keywords: Bioinstrumentation; Biotechnology; Mass spectrometers; Mass spectroscopy; Physiology; Spectroscopy.
Notes: AEROSPACE MEDICINE, VOL. 37, DEC. 1966, P. 1213-1217.
- FLIGHT RESULTS WITH A NON-AERODYNAMIC, VARIABLE STABILITY, FLYING PLATFORM , Conference Paper
Authors: Donald L. Mallick, Emil E. Kluever and Gene J. Matranga
Report Number: H-444
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Research and operational results obtained with nonaerodynamic variable stability flying platform for examining problem associated with lunar landing.
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Report Date: January 1966
No. Pages: 24
Keywords: Aerodynamic stability; Attitude control; Conferences; Flying platforms; Lunar landing.
Notes: SOCIETY OF EXPERIMENTAL TEST PILOTS, SYMPOSIUM, 10TH, BEVERLY HILLS, CALIF., SEP. 23, 24, 1966, PAPER./ SOCIETY OF EXPERIMENTAL TEST PILOTS, TECHNICAL REVIEW, VOL. 8, NO. 2, 1966, P. 98-121.
- FLIGHT TESTS OF A WIDE-ANGLE, INDIRECT OPTICAL VIEWING SYSTEM IN A HIGH-PERFORMANCE JET AIRCRAFT , Technical Note
Authors: G. P. Layton, Jr. and W. H. Dana
Report Number: NASA-TN-D-3690
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A wide-angle, indirect optical viewing system was qualitatively evaluated in an F-104B aircraft as a means of providing visual reference to the pilot. Safe and acceptable performance using the indirect viewing system was demonstrated for all phases of daytime visual flight. Landings were performed in both the conventional and low lift-drag-ratio configurations. When the horizon was in the field of view, aircraft attitude sensing with the optics was satisfactory about all axes except pitch attitude in climbing flight. This degraded pitch-attitude sensing was due to the poor resolution at the bottom of the field and the lack of view to the sides. A night flight was also performed. The system, in its present form, was considered unacceptable for this use because of large light losses and degraded resolution. It was evident in the study that additional view directly to the side is required for performing circling approaches.
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Report Date: October 1966
No. Pages: 35
Keywords: Aircraft performance; F-104 aircraft; Flight tests; Jet aircraft; Optics.
- AN EVALUATION OF THE HANDLING QUALITIES OF SEVEN GENERAL-AVIATION AIRCRAFT , Technical Note
Authors: M. R. Barber, C. K. Jones, T. R. Sisk and F. W. Haise
Report Number: NASA-TN-D-3726
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A review of existing criteria indicated that the criteria have not kept pace with aircraft development in the areas of dutch roll, adverse yaw, effective dihedral, and allowable trim changes with gear, flaps, and power. This study indicated that criteria should be specified for control-system friction and control-surface float. Furthermore, this program suggests a method of quantitatively evaluating the handling qualities of aircraft by the use of a pilot-workload factor.
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Report Date: November 1966
No. Pages: 58
Keywords: Aircraft control; Aircraft safety; Airspeed; Controllability; General aviation aircraft.
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