Accession Number:

ADA277487

Title:

Response of a Cantilevered Plate in Supersonic Flow

Descriptive Note:

Interim rept. Jan 93-Feb 94,

Corporate Author:

WRIGHT LAB WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1994-02-01

Pagination or Media Count:

54.0

Abstract:

The response of a thin rectangular panel to supersonic flow over its upper surface is investigated. The panel is fabricated of an isotropic material and has a constant thickness. The panel is fixed along one side such that the flow passes over its freely supported leading and trailing edges parallel to the fixed edge. A Rayleigh-Ritz method is applied to determine the in-plane and transverse response of the panel. The panel deflections either decay to a zero equilibrium or grow to a limited amplitude oscillation once the transients have decayed depending on the panel and flow parameters. At some combination of panel and flow parameters, the panel will begin to oscillate harmonically about a buckled state. Further increasing the flow conditions will cause the panel to either oscillate periodically about a buckled state or nonperiodically. The steady state response is dependent on the flow conditions and the initial deflections and velocity profiles of the panel. The flow Mach number and panel length-to-width ratios were varied. the cantilevered panel response is compared to previous research. A simply supported panel is briefly discussed and its response is also compared to previous work.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE