Sweepback Theory for Shock Waves at Hypersonic Speeds.

摘要

The report presents the results of hypersonic smalldeflection theory for the pressure coefficient, density, and other characteristics behind the shock wave on a sweptback wedge. The results have application to computation of the pressure on sweptback wings of wedge cross-section outside the region of influence of the tips. They can also be used to estimate the lift of a flat delta wing flying at very high speeds. In addition, the behavior of the shock waves deduced here is the first step in computing non-uniform flow fields behind the shock wave.