Summary of the 1/4-Scale SST Intake/Engine Interaction Test in the AEDC 16 ft Transonic Wind Tunnel,

Abstract

Wind tunnel tests were conducted on a 1/4-scale model of an early SST axisymmetric translating centerbody intake configuration over a Mach number range from 0.6 to 1.5. The intake was fitted either with a G.E. J85 turbojet engine or a cold pipe configuration. The intake and engine were highly instrumented with over 550 steady-state and 110 high-response data channels. Test program objectives included (1) determination of basic intake/engine interaction effects, (2) development of design criteria for prediction of these effects, (3) gathering of data to substantiate theoretical predictions of intake transients due to rapid changes in engine conditions, (4) corroboration of theoretical and empirical predictions of intake acoustic resonance phenomena, and (5) verification of the bypass door control concept. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 08, 1970
Accession Number
AD0874691

Entities

People

  • R. P. Grippe

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Acoustic Resonance
  • Design Criteria
  • Engines
  • Mach Number
  • Resonance
  • Scale Models
  • Steady State
  • Transonic Wind Tunnels
  • Turbojet Engines
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Psychology

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Fluid Dynamics.