Accession Number:

ADA012695

Title:

The Unsteady Aerodynamic Response of an Airfoil Cascade to a Time-Variant Supersonic Inlet Flow Field.

Descriptive Note:

Interim rept. 1 Apr 74-31 Mar 75,

Corporate Author:

INDIANAPOLIS CENTER FOR ADVANCED RESEARCH IND

Report Date:

1975-06-01

Pagination or Media Count:

53.0

Abstract:

A time-variant supersonic inlet flow with a subsonic axial component cascade experiment is described wherein the time-dependent phenomena are quantitatively determined. The cascade inlet unsteadiness was generated by harmonically oscillating the wedge which sets the inlet flow field to the cascade test section in a torsional mode through plus or minus 1 degree at frequencies ranging from 80 to 270 Hertz. Miniature high response pressure transducers mounted on the tunnel sidewall and imbedded in one of the cascaded airfoils were used to quantitatively measure the amplitude of the pressure disturbance, its frequency, and the phase difference between the unsteady pressures and the wedge motion.

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE