Accession Number:

ADA179858

Title:

Visid/Inviscid Separated Flows.

Descriptive Note:

Final rept. Sep 83-Mar 86,

Corporate Author:

MCDONNELL AIRCRAFT CO ST LOUIS MO

Report Date:

1986-07-01

Pagination or Media Count:

94.0

Abstract:

A method has been developed for calculating subsonic three-dimensional flows over fighter aircraft configurations at flow conditions including separation. The method employs a viscid inviscid interaction approach, with a panel method used for the inviscid analysis and a finite difference boundary layer method for the viscous analysis. The viscid and inviscid analyses are coupled using an interactive technique based on inverse boundary layer theory. This approach allows efficient calculation of flows with large separation regions, including both leading and trailing edge separations. The method was validated on three fighter aircraft geometries and comparisons with test data are presented. Keywords Jet fighters Separated flow Viscidinviscid interactions Interactive boundary layer theory Wing-body geometry Subsonic flow.

Subject Categories:

  • Fluid Mechanics
  • Computer Programming and Software

Distribution Statement:

APPROVED FOR PUBLIC RELEASE