The effect of forward speed on J85 engine noise from suppressor nozzles as measured in the NASA-Ames 40- by 80-foot wind tunnel
National Aeronautics and Space Administration, 1977 - Transportation - 62 pages
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104-tube nozzle 160 ACOUST1C ANGLE 32 Spoke 80-Foot Wind Tunnel ACOUST1C ANGLE REFERENCED acoustic angle acoustic data acoustic shroud AIE nozzle aircraft model Aircraft Noise airframe Ames Research Center auxiliary inlet ejector centerline Comparison of wind-tunnel conical ejector nozzle conical nozzle corrected for convection data measured data show Data type Nozzle data were corrected determine the effect Doppler shift effect of forward engine inlet axis engine power setting far-field directivity flight data forward quadrant noise ground reflections J85 ENGINE Jet Noise Lewis Research Center m/sec ft/sec microphone positions nacelle under wing NASA near-field noise measurements noise vs relative nozzle without shroud nozzles were tested outdoor static test peak noise angle PNL directivity radius arc reduced relative velocity shows data shroud shows sound pressure level static outdoor Static Test Facility TUBE NOZZLE TUNNEL DATA velocity index wind-tunnel data wind-tunnel forward speed wind-tunnel tests wind-tunnel velocity wing installation