SWEEPBACK THEORY FOR SHOCK WAVES AT HYPERSONIC SPEEDS,

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.

Document Details

Document Type
Technical Report
Publication Date
Apr 04, 1958
Accession Number
AD0606864

Entities

People

  • J. D. Cole

Organizations

  • RAND Corporation

Tags

DTIC Thesaurus Topics

  • Coefficients
  • Computations
  • Delta Wings
  • Flow
  • Flow Fields
  • Shock
  • Shock Waves
  • Sweptback Wings
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow