Dryden Technical Report Server
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- PRESSURES MEASURED IN FLIGHT ON THE AFT FUSELAGE AND EXTERNAL NOZZLE OF A TWIN-JET FIGHTER , Technical Paper
Authors: J. Nugent, T. J. Plant and N. V. Taillon
Report Number: NASA-TP-2017
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Fuselage, boundary layer, and nozzle pressures were measured in flight for a twin jet fighter over a Mach number range from 0.60 to 2.00 at test altitudes of 6100, 10,700, and 13,700 meters for angles of attack ranging from 0 deg to 7 deg. Test data were analyzed to find the effects of the propulsion system geometry. The flight variables, and flow interference. The aft fuselage flow field was complex and showed the influence of the vertical tail, nacelle contour, and the wing. Changes in the boattail angle of either engine affected upper fuselage and lower fuselage pressure coefficients upstream of the nozzle. Boundary layer profiles at the forward and aft locations on the upper nacelles were relatively insensitive to Mach number and altitude. Boundary layer thickness decreased at both stations as angle of attack increased above 4 deg. Nozzle pressure coefficient was influenced by the vertical tail, horizontal tail boom, and nozzle interfairing; the
last two tended to separate flow over the top of the nozzle from flow over the bottom of the nozzle. The left nozzle axial force coefficient was most affected by Mach number and left nozzle boattail angle. At Mach 0.90, the nozzle axial force coefficient was 0.0013.
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Subject Category: 02
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Report Date: May 1983
No. Pages: 90
Keywords: Boundary layers; Fighter aircraft; Fuselages; Nozzle flow; Nozzle geometry; Pressure measurement
- PRELIMINARY EXPERIENCE WITH A STEREOSCOPIC VIDEO SYSTEM IN A REMOTELY PILOTED AIRCRAFT APPLICATION , Technical Memorandum
Authors: T. W. Rezek
Report Number: NASA-TM-84909
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Remote piloting video display development at the Dryden Flight Research Facility of NASA's Ames Research Center is summarized, and the reasons for considering stereo television are presented. Pertinent equipment is described. Limited flight experience is also discussed, along with recommendations for further study.
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Subject Category: 06
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Report Date: September 1983
No. Pages: 14
Keywords: Aircraft equipment; Binocular vision; Display devices; Remotely piloted vehicles; Stereo television; Video equipment
- FLIGHT EVALUATION OF THE DEEC SECONDARY CONTROL AIR-START CAPABILITY , Technical Memorandum
Authors: J. B. Johnson and J. Nelson
Report Number: NASA-TM-84910
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The air-start capability of a secondary engine control (SEC) was tested for a DEEC-equipped F100 engine and installed in an F-15 airplane. Two air-start schedules were tested. The first was referred to as the group I schedule; the second or revised schedule was the group II start schedule. Using the group I start schedule, an airspeed of 300 knots was required to ensure successful 40- and 25-percent SEC-mode air starts. If N2 were less than 40 percent, a stall would occur when the start bleeds closed 40 sec after initiation of the air start. All JFS-assisted air starts were successful with the group start schedule. For the group II schedule, the time between pressurization and start-bleed closure ranged between 50 and 72 sec depending on altitude. All air starts were successful above 225 knots givin a 75-knot reduction in required airspeed for a successful air start. Spooldown air starts of 40 percent were successful at 200 knots at altitudes up to
10,650 m and at 175 knots at altitudes up to 6100 m. Idle rpm was lower than the desired 65 percent for air starts at higher altitudes and lower airspeeds. All JSF-assisted air starts were successful.
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Subject Category: 07
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Report Date: December 1983
No. Pages: 21
Keywords: Air start; Aircraft control; Digital systems; Digital techniques; Engine tests; F-15 aircraft; Flight tests
- UNMANNED VEHICLE SYSTEMS EXPERIENCES AT THE DRYDEN FLIGHT RESEARCH FACILITY , Technical Memorandum
Authors: T. W. Rezek
Report Number: NASA-TM-84913
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An overview is presented of the remotely piloted research vehicle (RPRV) activities at the NASA Dryden Flight Research Facility from their beginning to the present. The development of RPRV's as flight test tools is discussed, and system configuration is presented. Solutions derived from human factors experience related to flight activities and pilot responses have contributed to overall system capability. The development and use of visual displays, which are a critical feature of successful RPRV flights, are discussed as well as directions for future RPRV efforts.
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Subject Category: 05
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Report Date: January 1983
No. Pages: 22
Keywords: Display devices; Flight tests; Human factors engineering; Remotely piloted vehicles; Training devices
Notes: Presented at the AUVS-83 Symp. Unmanned Systems: Confidence for the 80's, Salt Lake City, 28-30 Jun. 1983.
- NASA B-57B SEVERE STORMS FLIGHT PROGRAM , Technical Memorandum
Authors: W. D. Painter and D. W. Camp
Report Number: NASA-TM-84921
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The B-57B Severe Storms Flight Program gathers data to characterize atmosphere anomalies such as wind shear, turbulence, and microbursts at altitudes up to 1000 feet (300 meters). These data are used to enhance the knowledge of atmospheric processes, to improve aviation safety, to develop systems technology and piloting technique for avoiding hazards and to increase the understanding of the causes of related aircraft accidents. The NASA Dryden Flight Research Facility B-57B aircraft has participated in several severe storms data collection programs such as the Joint Airport Weather Studies (JAWS) located in Denver, Colorado area, Operation Rough Rider located in the Norman, Oklahoma area with the National Severe Storms Laboratory, and Mountain and desert turbulence in the Edwards Air Force Base, California area. Flight data are presented from flights which encountered the wind shear, turbulence and microburst anomalies. These flight results are
discussed and some conclusions are made relating to these atmospheric anomalies.
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Subject Category: 03
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Report Date: December 1983
No. Pages: 25
Keywords: Meteorological research aircraft; Storms (meteorology); Weather forecasting; Aircraft accidents; Aircraft safety; Atmospheric turbulence; Data acquisition; Gust loads; Microbursts (meteorology); Wind shear; Wind velocity
- AFTI/F-16 FLIGHT TEST RESULTS AND LESSONS , Technical Memorandum
Authors: S. D. Ishmael and D. R. McMonagle
Report Number: NASA-TM-84920
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The advanced fighter technology integration (AFTI) F-16 aircraft is a highly complex digital flight control system integrated with advanced avionics and cockpit. The use of dissimilar backup modes if the primary system fails requires the designer to trade off system simplicity and capability. The tradeoff is evident in the AFTI/F-16 aircraft with its limited stability and fly by wire digital flight control systems when a generic software failure occurs the backup or normal mode must provide equivalent envelop protection during the transition to degraded flight control. The complexity of systems like the AFTI/F-16 system defines a second design issue, which is divided into two segments: (1) the effect on testing, (2) and the pilot's ability to act correctly in the limited time available for cockpit decisions. The large matrix of states possible with the AFTI/F-16 flight control system illustrates the difficulty of both testing the system and choosing
real time pilot actions. The third generic issue is the possible reductions in the user's reliability expectations where false single channel information can be displayed at the pilot vehicle interface while the redundant set remains functional.
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Subject Category: 08
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Report Date: October 1983
No. Pages: 30
Keywords: Avionics; Control theory; Flight control; Synchronism; Systems engineering
Notes: Presented at the 27th Symp. of the Soc. of Exptl. Test Pilots, Beverly Hills, Calif., 28 Sep. - 1 Oct. 1983.
- FLIGHT EVALUATION RESULTS FOR A DIGITAL ELECTRONIC ENGINE CONTROL IN AN F-15 AIRPLANE , Conference Paper
Authors: F. W. Burcham, Jr., L. P. Myers and K. R. Walsh
Report Number: H-1208
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A digital electronic engine control (DEEC) system on an F100 engine in an F-15 airplane was evaluated in flight. Thirty flights were flown in a four-phase program from June 1981 to February 1983. Significant improvements in the operability and performance of the F100 engine were developed as a result of the flight evaluation: the augmentor envelope was increased by 15,000 ft, the airstart envelope was improved by 75 knots, and the need to periodically trim the engine was eliminated. The hydromechanical backup control performance was evaluated and was found to be satisfactory. Two system failures were encountered in the test program; both were detected and accommodated successfully. No transfers to the backup control system were required, and no automatic transfers occurred. As a result of the successful DEEC flight evaluation, the DEEC system has entered the full-scale development phase.
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Subject Category: 07
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Report Date: November 1983
No. Pages: 11
Keywords: Avionics; Digital techniques; Electronic control; Engine control; F-15 aircraft; In-flight monitoring
Notes: AIAA, AHS, IES, SETP, SFTE, and DGLR, Flight Testing Conference, 2nd, Las Vegas, NV, Nov. 16-18, 1983.
- PROJECT MANAGEMENT TECHNIQUES FOR HIGHLY INTEGRATED PROGRAMS , Technical Memorandum
Authors: J. F. Stewart and C. A. Bauer
Report Number: NASA-TM-86023
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The management and control of a representative, highly integrated high-technology project, in the X-29A aircraft flight test project is addressed. The X-29A research aircraft required the development and integration of eight distinct technologies in one aircraft. The project management system developed for the X-29A flight test program focuses on the dynamic interactions and the the intercommunication among components of the system. The insights gained from the new conceptual framework permitted subordination of departments to more functional units of decisionmaking, information processing, and communication networks. These processes were used to develop a project management system for the X-29A around the information flows that minimized the effects inherent in sampled-data systems and exploited the closed-loop multivariable nature of highly integrated projects.
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Subject Category: 81
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Report Date: December 1983
No. Pages: 13
Keywords: Decision making; Management planning; Project management; Control theory; Feedback control; Systems analysis
Notes: Presented at the 2nd Flight Test Conference, Las Vegas, Nevada, 16-18 Nov. 1983.
- IN-FLIGHT LOAD TESTING OF ADVANCED SHUTTLE THERMAL PROTECTION SYSTEMS , Technical Memorandum
Authors: B. M. Trujillo, R. Meyer, Jr. and P. M. Sawko
Report Number: NASA-TM-86024
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NASA Ames Research Center has conducted in-flight airload testing of some advanced thermal protection systems (TPS) at the Dryden Flight Research Center. The two flexible TPS materials tested, felt reusable surface insulation (FRSI) and advanced flexible reusable surface insulation (AFRSI), are currently certified for use on the Shuttle orbiter. The objectives of the flight tests were to evaluate the performance of FRSI and AFRSI at simulated launch airloads and to provide a data base for future advanced TPS flight tests. Five TPS configurations were evaluated in a flow field which was representative of relatively flat areas without secondary flows. The TPS materials were placed on a fin, the Flight Test fixture (FTF), that is attached to the underside of the fuselage of an F-104 aircraft. This paper describes the test approach and techniques used and presents the results of the advanced TPS flight test. There were no failures noted during
post-flight inspections of the TPS materials which were exposed to airloads 40 percent higher than the design launch airloads.
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Subject Category: 18
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Report Date: December 1983
No. Pages: 13
Keywords: Aerodynamic loads; In-flight monitoring; Load tests; Space shuttle orbiters; Thermal protection
Notes: Presented at 2nd AIAA Flight Test Conference, Las Vegas, Nevada, 16-18 Nov. 1983.
- AD-1 OBLIQUE WING RESEARCH AIRCRAFT PILOT EVALUATION PROGRAM , Conference Paper
Authors: W. D. Painter
Report Number: H-1215
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight test program of a low cost, low speed, manned, oblique wing research airplane was conducted at the NASA Dryden Flight Research Facility in cooperation with NASA Ames Research Center between 1979 and 1982. When the principal purpose of the test program was completed, which was to demonstrate the flight and handling characteristics of the configuration, particularly in wing-sweep-angle ranges from 45 to 60 deg, a pilot evaluation program was conducted to obtain a qualification evaluation of the flying qualities of an oblique wing aircraft. These results were documented for use in future studies of such aircraft.
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Subject Category: 05
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Report Date: October 1983
No. Pages: 18
Keywords: Aerodynamic configurations; Flight characteristics; Flight tests; Oblique wings; Research aircraft
Notes: American Institute of Aeronautics and Astronautics, Aircraft Design, Systems and Technology Meeting, Fort Worth, TX, Oct. 17-19, 1983.
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