Accession Number:

ADA070232

Title:

The Oblique Wing as a Lifting-Line Problem in Transonic Flow.

Descriptive Note:

Technical rept.,

Corporate Author:

UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES DEPT OF AEROSPACE ENGINEERING

Personal Author(s):

Report Date:

1979-05-01

Pagination or Media Count:

113.0

Abstract:

A transonic-flow theory of thin oblique wing of high aspect ratio is presented, which permits a delineation of the influence of wing sweep, centerline curvature, and other three-dimensional 3-D effects on the nonlinear mixed flow in the framework of an asymptotic theory. The component flow near the wing section is basically plane two-dimensional but nonlinear and mixed, being governed by equations consistent with the transonic small-disturbance approximation. The work analyzes 3-D corrections to this nonlinear problem and matching its solutions to that of a outer flow. In the parameter domain of interest, the outer solutions correspond to a high subsonic, or a linear sonic, outer flow, representable by a Prandtl-Glauert solution involving a swept or curved lifting line in the leading approximation. A procedure based on a line relaxation method for solving numerically the reduced inner problem is described solutions with high subcritical, as well as slightly supercritical, component flows are demonstrated. Comparison with corresponding numerical solutions based on full-potential equations for oblique elliptic wing shows encouraging agreement.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE