AIAA 75-436 - AIAA 75-481

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American Institute of Aeronautics and Astronautics, 1975 - Aerodynamics noise

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acoustic AIAA airfoil analysis angle appears approximately axial axis band blade boundary calculated changes characteristics Comparison component configuration correlation deflection dependence diameter direction discussed distance distribution duct edge effects engine equation exhaust exit experiment experimental field Figure flap flight flow fluctuating forward frequency function fundamental given harmonics higher increase indicate inlet intensity interaction jet noise layer length levels lift force Mach number mean measured mechanism microphone modes noted nozzle observed obtained peak plane position prediction present PRESSURE LEVEL propagation radiation range ratio reduction Reference region relative rotational rotor scale shear shown shown in Figure shows signal similar sound pressure spacing spectra spectrum speed static stator surface theoretical theory thrust tion tip speed tone trailing tunnel turbine turbulence velocity vortex wake wave wing

Bibliographic information

TitleAIAA 75-436 - AIAA 75-481
Volume 1 of AIAA 2nd Aero-Acoustics Conference: Hampton, Va., March 24-26, 1975, American Institute of Aeronautics and Astronautics
ContributorAmerican Institute of Aeronautics and Astronautics
PublisherAmerican Institute of Aeronautics and Astronautics, 1975
Original fromPennsylvania State University
DigitizedJul 21, 2010
  
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