Accession Number:

AD0874691

Title:

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

Descriptive Note:

Corporate Author:

BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV

Personal Author(s):

Report Date:

1970-05-08

Pagination or Media Count:

32.0

Abstract:

Wind tunnel tests were conducted on a 14-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 intakeengine 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

Subject Categories:

  • Civilian Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE