SUPERSONIC FLOW AROUND CONES AT LARGE YAW,

Abstract

Equations were developed for the flow properties in the region bounded by a supersonic cone body at large angle of attack and its attached shock wave, for use with the tabulations of Kopal. A comparison of the theoretical results is made with the experimental data of Cronvich. A slight discrepancy which increases with increasing Mach number was found in the value of K sub DYH, the yawing head drag as tabulated by Kopal. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 06, 1951
Accession Number
AD0604291

Entities

People

  • C. P. Siska
  • G. B. W. Young

Organizations

  • RAND Corporation

Tags

DTIC Thesaurus Topics

  • Equations
  • Experimental Data
  • Flow
  • Mach Number
  • Shock
  • Shock Waves
  • Supersonic Flow
  • Waves

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow