Accession Number:

AD0606864

Title:

SWEEPBACK THEORY FOR SHOCK WAVES AT HYPERSONIC SPEEDS,

Descriptive Note:

Corporate Author:

RAND CORP SANTA MONICA CALIF

Personal Author(s):

Report Date:

1958-04-04

Pagination or Media Count:

8.0

Abstract:

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.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE