Accession Number:

ADA065632

Title:

A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings.

Descriptive Note:

Final rept.,

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1978-09-01

Pagination or Media Count:

233.0

Abstract:

A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges.

Subject Categories:

  • Aircraft
  • Numerical Mathematics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE