Prediction of Aerodynamic Characteristics of Fighter Wings at High Angles of Attack.
Abstract
Potential modeling techniques for representing separated and vortical flows are investigated with the objective being the prediction of aerodynamic characteristics of fighter wings at high angles of attack. A low-order surface singularity panel method is coupled with iterative routines for locating the force free wake and for including viscous effects and edge vortices. The viscous effects are computed using integral boundary layer procedures and the displacement effect is represented in the panel method using the transpiration model. Regions of massive separation are enclosed in free vortex sheets which are included in the general wake configuration scheme of the panel method. Calculations show encouraging results in those cases where there is little cross flow inside the separated zone. The calculations were less successful when the separated zone became highly three-dimensional, as in the case of a vortex/surface interaction. The modeling technique promises to be a practical, cost effective approach to predicting the aerodynamic characteristics of fighter wings at high angle of attack; however, further development of the model is required for the highly three-dimensional separated zones involving strong vortical action. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1984
- Accession Number
- ADA145107
Entities
People
- B. Maskew
- F. A. Dvorak
- J. K. Nathman
- T. S. Vaidyanathan