Euler Solutions of Supersonic Wing-Body Interference at High Incidence Including Vortex Effects.
Abstract
The purpose of this investigation was to demonstrate how the flow field about a supersonic wing-body combination can be calculated using the Euler equations when body vortices are present as well as separation vortices from the sharp leading edges of the wing panels. In order to start the calculations in the supersonic marching mode, it was necessary to develop solutions for cones with separated flow. Data on the separation line locations for circular cones were correlated to provide boundary conditions for this purpose. A series of calculations for a wing-body combination with delta wings at Mach numbers of 3, 4, and 5 and angles of attack up to 25 deg was made to demonstrate the feasibility of the use of the Euler equations to handle separated rotational flows. Some comparisons with experimental pressure distributions and fin load were made with good agreement. The Euler code was used to evaluate the accuracy of a panel method for calculating the wing-body pressure distributions as influenced by body vortices. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1982
- Accession Number
- ADA120216
Entities
People
- Gary D. Kuhn
- Goetz H. Klopfer
- Jack N. Nielsen
Organizations
- Nielsen Engineering & Research (United States)