ON THE USE OF IMPACT THEORY FOR SLENDER CONFIGURATIONS EXHIBITING FLOW SEPARATION
Abstract
A method is presented for predicting analytically the non-linear variation of normal force with angle of attack for very slender wing-body combinations exhibiting flow separation. The method is based on the cross-flow drag concept and employs Newtonian impact theory in two dimensions to calculate the cross-flow drag coefficient. It is demonstrated that this theory shows good agreement with experiment for two-dimensional incompressible flow past bluff shapes. Further more, the analytical expression for the flat plate agrees exactly with the theoretical analysis of Bollay. Mathematical expressions are developed for the normal force on a conical slender wing-body combination with elliptical body of arbitrary eccentricity. Calculations are compared with experimental normal forces on wing body combinations at supersonic speeds and on delta wings at subsonic speeds. The agreement appears to be very good over a wide range of angle of attack, provided that the slenderness approximation is satisfied and that separation occurs near the lateral extremities of the configuration in question.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 31, 1963
- Accession Number
- AD0406468
Entities
People
- Alvin H. Sacks
- Jack A. Burnell