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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (17)
  • 2015-2019
  • 1985-1989  (7)
  • 1980-1984  (10)
  • 1
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    Summary of results of NASA F-15 flight research program (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA conducted a multidisciplinary flight research program on the F-15 airplane. The program began in 1976 when two preproduction airplanes were obtained from the U.S. Air Force. Major projects involved stability and control, handling qualities, propulsion, aerodynamics, propulsion controls, and integrated propulsion-flight controls. Several government agencies and aerospace contractors were involved. In excess of 330 flights were flown, and over 85 papers and reports were published. This document describes the overall program, the projects, and the key results. The F-15 was demonstrated to be an excellent flight research vehicle, producing high-quality results.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-9761
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight test of a decoupler pylon for wing/store flutter suppression (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The decoupler pylon is a NASA concept of passive wing-store flutter suppression achieved by providing a low store-pylon pitch frequency. Flight tests where performed on an F-16 airplane carrying on each wing an AIM-9J wingtip missile, a GBU-8 bomb near midspan, and an external fuel tank. Baseline flights with the GBU-8 mounted on a standard pylon established that this configuration is characterized by an antisymmetric limited amplitude flutter oscillation within the operational envelope. The airplane was then flown with the GBU-8 mounted on the decoupler pylon. The decoupler pylon successfully suppressed wing-store flutter thoughout the flight envelope. A 37-percent increase in flutter velocity over the standard pylon was demonstrated. Maneuvers with load factors to 4g were performed. Although the static store displacements during maneuvers were not sufficiently large to be of concern, a store pitch alignment system was tested and performed successfully. One GBU-8 was ejected demonstrating that weapon separation from the decoupler pylon is normal. Experience with the present decoupler pylon design indicated that friction in the pivoting mechanism could affect its proper functioning as a flutter suppressor.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-9730
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Ground vibration test of an F-16 airplane with modified decoupler pylons (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The decoupler pylon is a passive wing/store flutter suppression device. It was modified to reduce friction following initial flight tests. A ground vibration test was conducted on an F-16 aircraft loaded on each wing with a one-half-full (center bay empty) 370-gallon fuel tank mounted on a standard pylon, a GBU-8 store mounted on the decoupler pylon, and an AIM-9J missile mounted on a wingtip launcher. The test was conducted prior to flight tests with the modified pylon to determine modal frequencies, mode shapes, and structural damping coefficients. Data presented include frequency response plots, mode shape plots, and limited force-effect plots.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87634 , L-16065 , NAS 1.15:87634
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Minimum time and fuel flight profiles for an F-15 airplane with a Highly Integrated Digital Electronic Control (HIDEC) system (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simulation study was conducted to optimize minimum time and fuel consumption paths for an F-15 airplane powered by two F100 Engine Model Derivative (EMD) engines. The benefits of using variable stall margin (uptrim) to increase performance were also determined. This study supports the NASA Highly Integrated Digital Electronic Control (HIDEC) program. The basis for this comparison was minimum time and fuel used to reach Mach 2 at 13,716 m (45,000 ft) from the initial conditions of Mach 0.15 at 1524 m (5000 ft). Results were also compared to a pilot's estimated minimum time and fuel trajectory determined from the F-15 flight manual and previous experience. The minimum time trajectory took 15 percent less time than the pilot's estimate for the standard EMD engines, while the minimum fuel trajectory used 1 percent less fuel than the pilot's estimate for the minimum fuel trajectory. The F-15 airplane with EMD engines and uptrim, was 23 percent faster than the pilot's estimate. The minimum fuel used was 5 percent less than the estimate.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86042 , H-1242 , NAS 1.15:86042
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Ground vibration test of the laminar flow control JStar airplane (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A ground vibration test was conducted on a Lockheed JetStar airplane that had been modified for the purpose of conducting laminar flow control experiments. The test was performed prior to initial flight flutter tests. Both sine-dwell and single-point-random excitation methods were used. The data presented include frequency response functions and a comparison of mode frequencies and mode shapes from both methods.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86398 , L-15949 , NAS 1.15:86398
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Computer studies of hybrid-slotted working sections with minimum interference at subsonic speeds (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of computations on tunnel boundary-interference effects for hybrid-slotted working sections was performed using the WALINT code. The slots were modeled as lines of porosity with linear crossflow characteristics. The basic shape evaluated was for a rectangular section with height-to-width ratio = 0.835 and its companion in the duplex mode (half model testing) with height-to-width ratio = 0.6. A best overall basic configuration was determined with seven slots on each wall with open area ratio on each wall of 17.5%. For both full-span and half-model testing, the optimum solution required closing all but two slots on each of the half-walls parallel to the plane of the wing (equivalent to four slots on the full floor and ceiling). The results are presented here for the best configurations and are shown to be within the figure-of-merit range of + or - 0.04 in upwash, and + or - 0.1 in curvature for the Mach number range 0.6 to 0.85. Blockage effects are shown to be small.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86002 , A-9845 , NAS 1.15:86002
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Ground vibration test of F-16 airplane with initial decoupler pylon (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A ground vibration test was conducted on an F-16 airplane loaded on each wing with a 370-gal tank mounted on a standard pylon, a GBU-8 store mounted on a decoupler pylon, and an AIM-9J missile mounted on a wing-tip launcher. The decoupler pylon is a passive wing/store flutter-suppression device. The test was conducted prior to initial flight tests to determine the modal frequencies, mode shapes, and structural damping coefficients. The data presented include frequency response plots, force effect plots, and limited mode shape data.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86259 , L-15782 , NAS 1.15:86259
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Flutter clearance of the horizontal tail of the Bellanca Skyrocket II airplane (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Skyrocket II is an all composite constructed experimental prototype airplane. A flutter clearance program was conducted on the horizontal tail so that the airplane could be safely flown to acquire natural laminar flow aerodynamic data. Ground vibration test data were used in a lifting surface flutter analysis to predict symmetric and antisymmetric flutter boundaries. Subcritical response data which were acquired during flight tests are compared with the analytical results. The final flutter clearance placard speed was based on flight test data.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84528 , L-15453 , NAS 1.15:84528
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Passive control of wing/store flutter (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: This paper presents results for a passive flutter suppression approach known as the decoupler pylon. The decoupler pylon dynamically isolates the wing from store pitch inertia effects by means of soft-spring/damper elements assisted by a low-frequency feedback-control system which minimizes static pitch deflections of the store due to maneuvers and changing flight conditions. Wind-tunnel tests and analyses show that this relatively simple pylon suspension system provides substantial increases in flutter speed and reduces the sensitivity of flutter to changes in store inertia and center-of-gravity location. Flutter characteristics of F-16 and YF-17 flutter models equipped with decoupler pylon-mount stores are presented and compared with results obtained on the same model configurations using active flutter suppression systems. These studies show both passive and active concepts to be effective in suppressing wing/store flutter. Also presented are data showing the influence of pylon stiffness nonlinearities on wing/store flutter.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: MD Aircraft Stores Compatibility Symposium; Sept. 9-11, 1980; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Aircraft aeroelasticity and structural dynamics research at the NASA Langley Research Center - Some illustrative results (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Highlights of nine different research studies are described. Five of these topics relate directly to fixed-wing aircraft and range from flutter studies using relatively simple and inexpensive wind-tunnel models to buffet studies of the vertical tails of an advanced high-performance configuration. The other four topics relate directly to rotary-wing aircraft and range from studies of the performance and vibration characteristics of an advanced rotor design to optimization of airframe structures for vibration attenuation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ICAS Congress; Aug 28, 1988; Jerusalem; Israel
    Format: text
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    NASA TECHNICAL REPORTS
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