Accession Number:

ADA030883

Title:

Analytical and Experimental Investigations of Delta Wings in Incompressible Flow

Descriptive Note:

Final technical rept. 1 Jan-31 Dec 1976

Corporate Author:

TEXAS A AND M RESEARCH FOUNDATION COLLEGE STATION

Personal Author(s):

Report Date:

1976-08-01

Pagination or Media Count:

92.0

Abstract:

The theoretical analysis of delta wings in incompressible flow is created by a numerical lifting-surface theory based upon a velocity potential formulation. This theory has been expanded to include spanwise velocity effects and the leading-edge departion associated with delta wings. The numerical technique has made use of both fixed and free wakes. In the fixed-wake model, the analytical results of Brown and Michael have been used to position the leading-edge vortex. In the more refined free-wake model, the leading edge separation was modeled as a discrete number of vortices attached to the leading- edge, which are allowed to align themselves with streamlines. Experimental research included wind tunnel tests to determine the vortex location, vortex burst location, and upper surface pressure distribution on a delta wing, AR 2, in an oscillatory airstream.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE