X-20/624A AIR VEHICLE BUFFET TEST-SPO 203

Abstract

Aerodynamic noise data obtained from a transonic wind tunnel test of an X-20itan IIIC mo/del are reported. Measurements made at 28 test points on the X-20 payload only were designed to define the aerodynamic noise environments resulting from separated flow and fluctuating shock phenomena associated with transonic flight in the Mach number range 0.60 - 1.08. Angles of attack and yaw were varied within = 4 degrees. Reported data include over-all and one-third octave band sound pressure levels and space-correlation coefficients in the frequency range 40 - 2500 cps.

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Document Details

Document Type
Technical Report
Publication Date
Oct 11, 1963
Accession Number
AD0426251

Entities

People

  • M. D. Lockleer

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Noise
  • Aircrafts
  • Data Reduction
  • Dynamic Pressure
  • Frequency Response
  • Instrumentation
  • Mach Number
  • Phase Shift
  • Pressure Transducers
  • Sound Pressure
  • Tape Recorders
  • Test And Evaluation
  • Test Facilities
  • Three Dimensional
  • Transonic Wind Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Acoustics.
  • Aerodynamics/Aeronautics.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers