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

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)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1965
Accession Number
AD0478430

Entities

People

  • David R. Wiley
  • Michael G. Seidl

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Aerodynamic Noise
  • Deflection
  • Frequency
  • Instrumentation
  • Measurement
  • Microphones
  • Models
  • Noise
  • Pressure Measurement
  • Scale Models
  • Sound Pressure
  • Supersonic Wind Tunnels
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Acoustics.
  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow