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  • 1
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    Real-time pilot guidance system for improved flight-test maneuvers (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The real-time pilot display uplink development at the Dryden Flight Research Facility is described, with a focus on recent F-104 studies. A nose boom gathers data on the Mach number, pressure altitude, and angle of attack. The system provides the pilot with guidance to improve maneuver accuracy and fly more complex trajectories. The uplink presents the pilot with computed differences between a reference flight path and actual flight state conditions, using a downlink to the ground where engineering computations are performed, feedback is transmitted, and corrections are applied. Details of the flight test trajectories and data from test results are provided for level turns, constant thrust turns, dynamic pressure trajectories, constant radar altitude accelerations and decelerations, and a Reynolds number trajectory. The system has proved capable of reducing pilot workload and saving fuel by decreasing the flight time necessary to obtain specific data.
    Keywords: AIRCRAFT INSTRUMENTATION
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Laminar flow integration: Flight tests status and plans (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Under the Aircraft Energy Efficiency - Laminar Flow Control Program, there are currently three flight test programs under way to address critical issues concerning laminar flow technology application to commercial transports. The Leading-Edge Flight Test (LEFT) with a JetStar aircraft is a cooperative effort with the Ames/Dryden Flight Research Facility to provide operational experience with candidate leading-edge systems representative of those that might be used on a future transport. In the Variable Sweep Transition Flight Experiment (VSTFE), also a cooperative effort between Langley and Ames/Dryden, basic transition data on an F-14 wing with variable sweep will be obtained to provide a data base for laminar flow wing design. Finally, under contract to the Boeing Company, the acoustic environment on the wing of a 757 aircraft will be measured and the influence of engine noise on laminar flow determined with a natural laminar flow glove on the wing. The status and plans for these programs are reported.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Langley Symposium on Aerodynamics, Volume 1; p 485-518
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight-Measured Aerodynamic Loads on a 0.92 Aspect Ratio Lifting Surface (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ventral fin loads, expressed as normal force coefficients, bending moment coefficients, and torque coefficients, were measured during flight tests of a YF-12A airplane. Because of the proximity of the ventral fin to the ailerons, the aerodynamic loads presented were the result of both sideslip loads and aileron crossflow loads. Aerodynamic data obtained from strain gage loads instrumentation and some flight pressure measurements are presented for several Mach numbers ranging from 0.70 to 2.00. Selected wind tunnel data and results of linear theoretical aerodynamic calculations are presented for comparison.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 73-91
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of winglets on a first-generation jet transport wing. 4: Stability characteristics for a full-span model at Mach 0.30 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static longitudinal and lateral directional characteristics of a 0.035 scale model of a first generation jet transport were obtained with and without upper winglets. The data were obtained for take off and landing configurations at a free stream Mach number of 0.30. The results generally indicated that upper winglets had favorable effects on the stability characteristics of the aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1119 , L-11705
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Drag reductions obtained by modifying a box-shaped ground vehicle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A box-shaped ground vehicle was used to simulate the aerodynamic drag of high volume transports, that is, delivery vans, trucks, or motor homes. The coast-down technique was used to define the drag of the original vehicle, having all square corners, and several modifications of the vehicle. Test velocities ranged up to 65 miles per hour, which provided maximum Reynolds numbers of 1 times 10 to the 7th power based on vehicle length. One combination of modifications produced a reduction in aerodynamic drag of 61 percent as compared with the original square-cornered vehicle.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-56027
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Real-time pilot guidance system for improved flight-test maneuvers (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Dryden Flight Research Facility has developed a pilot trajectory guidance system that is intended to increase the accuracy of flight-test data and decrease the time required to achieve and maintain desired test conditions, or both. The system usually presented to the pilot computed differences between reference or desired and actual flight state conditions. The pilot then used a cockpit display as an aid to acquire and hold desired test conditions. This paper discusses various flight-test maneuvers and the quality of data obtained using the guidance system. Some comparisons are made between the quality of maneuvers obtained with and without the system. Limited details of the guidance system and algorithms used are included. In general, the guidance system improved the quality of the maneuvers and trajectories flown, as well as allowing trajectories to be flown that would not have been possible without the system. This system has moved from the developmental stage to full operational use in various Dryden research and test aircraft.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: AIAA PAPER 83-2747
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    In-flight load testing of advanced thermal protection systems (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2704
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    A unique flight test facility - Description and results (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Dryden Flight Research Facility has developed a unique research facility for conducting aerodynamic and fluid mechanics experiments in flight. A low aspect ratio fin, referred to as the flight test fixture (FTF), is mounted on the underside of the fuselage of an F-104G aircraft. The F-104/FTF facility is described, and the capabilities are discussed. The capabilities include (1) a large Mach number envelope (0.4 to 2.0), including the region through Mach 1.0; (2) the potential ability to test articles larger than those that can be tested in wind tunnels; (3) the large chord Reynolds number envelope (greater than 40 million); and (4) the ability to define small increments in friction drag between two test surfaces. Data are presented from experiments that demonstrate some of the capabilities of the FTF, including the shuttle thermal protection system airload tests, instrument development, and base drag studies. Proposed skin friction experiments and instrument evaluation studies are also discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Council of the Aeronautical Sciences; Aug 22, 1982 - Aug 27, 1982; Seattle, WA
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    NASA TECHNICAL REPORTS
  • 9
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    In-flight aerodynamic load testing of the Shuttle thermal protection system (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: To contribute to the certification of the structural integrity of the Space Shuttle orbiter's thermal protection system (TPS) before the first Shuttle flight, in-flight aerodynamic load tests of six simulated areas of the orbiter were conducted. The tests were performed on an F-104 and F-15 aircraft. This paper describes the test approach, techniques used, and results. Two areas of the orbiter TPS were redesigned and retested as a result of these tests. No TPS failures due to air-loads occurred in the areas that were evaluated in the flight tests during the Shuttle's first flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-2468 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    A unique flight test facility: Description and results (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Dryden Flight Research Facility has developed a unique research facility for conducting aerodynamic and fluid mechanics experiments in flight. A low aspect ratio fin, referred to as the flight test fixture (FTF), is mounted on the underside of the fuselage of an F-104G aircraft. The F-104G/FTF facility is described, and the capabilities are discussed. The capabilities include (1) a large Mach number envelope (0.4 to 2.0), including the region through Mach 1.0; (2) the potential ability to test articles larger than those that can be tested in wind tunnels; (3) the large chord Reynolds number envelope (greater than 40 million); and (4) the ability to define small increments in friction drag between two test surfaces. Data are presented from experiments that demonstrate some of the capabilities of the FTF, including the shuttle thermal protection system airload tests, instrument development, and base drag studies. Proposed skin friction experiments and instrument evaluation studies are also discussed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-84900 , NAS 1.15:84900 , ICAS-PAPER-82-5.3.3 , Congr. of the Intern. Council of the Aeron. Sci. (ICAS)/AIAA Aircraft Systems and Technol. Conf.; Aug 22, 1982 - Aug 27, 1982; Seattle
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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