The Oblique Wing as a Lifting-Line Problem in Transonic Flow.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1979
- Accession Number
- ADA070232
Entities
People
- H. K. Cheng
- S. Y. Meng
Organizations
- University of Southern California