Item Details

Steady-State and Dynamic Pressure Phenomena in the Propulsion System of an F-111A Airplane

by Frank W. Burchham, Jr., Donald L. Hughes, and Jon K. Holzman
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973.
Language
English
Series
NASA Technical Note
Summary
Flight tests were conducted with two F-111A airplanes to study the effects of steady-state and dynamic pressure phenomena on the propulsion system. Analysis of over 100 engine compressor stalls revealed that the stalls were caused by high levels of instantaneous distortion. In 73 percent of these stalls, the instantaneous circumferential distortion parameter, k sub theta, exhibited a peak just prior to stall higher than any previous peak. The K sub theta parameter was a better indicator of stall than the distortion factor, k sub d, and the maximum-minus-minimum distortion parameter, d, was poor indicator of stall. Inlet duct resonance occurred in both F-111A airplanes and is believed to have been caused by oscillations of the normal shock wave from an internal to an external position. The inlet performance of the two airplanes was similar in terms of pressure recovery, distortion, and turbulence, and there was good agreement between flight and wind-tunnel data up to a Mach number of approximately 1.8.
Description
iv, 98 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at the NASA Flight Research Center.
  • Cover title.
  • Bibliography: p. 22-23.
Series Statement
NASA technical note ; NASA TN D-7328
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Burcham, Frank W.
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    a| Steady-state and dynamic pressure phenomena in the propulsion system of an F-111A airplane c| by Frank W. Burchham, Jr., Donald L. Hughes, and Jon K. Holzman.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1973.
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    a| iv, 98 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| NASA TN D-7328
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    a| Prepared at the NASA Flight Research Center.
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    a| Cover title.
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    a| Bibliography: p. 22-23.
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    a| Flight tests were conducted with two F-111A airplanes to study the effects of steady-state and dynamic pressure phenomena on the propulsion system. Analysis of over 100 engine compressor stalls revealed that the stalls were caused by high levels of instantaneous distortion. In 73 percent of these stalls, the instantaneous circumferential distortion parameter, k sub theta, exhibited a peak just prior to stall higher than any previous peak. The K sub theta parameter was a better indicator of stall than the distortion factor, k sub d, and the maximum-minus-minimum distortion parameter, d, was poor indicator of stall. Inlet duct resonance occurred in both F-111A airplanes and is believed to have been caused by oscillations of the normal shock wave from an internal to an external position. The inlet performance of the two airplanes was similar in terms of pressure recovery, distortion, and turbulence, and there was good agreement between flight and wind-tunnel data up to a Mach number of approximately 1.8.
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    a| Mode of access: Internet.
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    a| F-111 (Jet fighter plane)
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    a| Airplanes x| Turbofan engines x| Testing.
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    a| Jet engines x| Air intakes.
    650
      
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    a| Airplanes x| Jet propulsion.
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    a| Holzman, Jon K.
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    a| Hughes, Donald L. q| (Donald Lee), d| 1926-
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Flight Research Center (U.S.)
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