Accession Number : AD0478430

Title :   AERODYNAMIC NOISE TESTS ON X-20 SCALE MODELS. VOLUME I. DATA REPORT.

Descriptive Note : Final rept. Oct 64-Aug 65,

Corporate Author : BOEING CO SEATTLE WASH AEROSPACE GROUP

Personal Author(s) : Seidl ,Michael G. ; Wiley,David R.

Report Date : NOV 1965

Pagination or Media Count : 490

Abstract : Aerodynamic noise data are reported for tests conducted on a 1/15-scale X-20 model in the 2 transonic and supersonic wind tunnels, and on a 1/15-scale X-20/624A model in another transonic tunnel. Measurements are reported for 16 microphone positions on the model in the transonic and supersonic tunnel tests, and 18 positions for the other transonic tunnel tests. The total Mach range spanned during the tests was 0.5 to 3.5. Angle of attack varied from -10 to +18, yaw angle from -4 to +4deg, elevon deflection from -30 to + 10 deg, and rudder deflection from -30 to + 35 deg. The data are reported in the form of curves showing octave-band sound pressure level versus frequency, over the octave-band-center frequency range of 16 to 2000 cycles per second. Brief descriptions of instrumentation and basic test procedures are presented. (Author)

Descriptors :   (*BOOST GLIDE VEHICLES, NOISE), WIND TUNNEL MODELS, MODEL TESTS, PERFORMANCE(ENGINEERING), TRANSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, ANGLE OF ATTACK, YAW, ELEVONS, DEFLECTION, AERIAL RUDDERS, SOUND, PRESSURE, FREQUENCY, INSTRUMENTATION, TEST METHODS, ACOUSTICS, FLOW SEPARATION, SHOCK WAVES, OSCILLATION, BOUNDARY LAYER, VIBRATION, EXPERIMENTAL DATA

Subject Categories : Aerodynamics
      Acoustics
      Unmanned Spacecraft
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE