CURVES OF SHOCKWAVE, EXPANSION WAVE AND SKIN FRICTION DATA FOR HYPERSONIC SPEEDS

Abstract

This report presents curves of shockwave, expansion wave and boundary layer data plotted for use at Mach numbers up to 20. Normal and oblique shockwave parameters, conical shock parameters, expansion wave parameters, cone aerodynamic coefficients and compressible laminar and turbulent boundary layer skin friction formulas are given for Mach numbers up to at least 20. The use of these curves is briefly described in the text.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 15, 1954
Accession Number
AD0833215

Entities

People

  • M. F. Romig

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Birds
  • Boundaries
  • Boundary Layer
  • Coefficients
  • Corporations
  • Drag
  • Equations
  • Flow
  • Friction
  • Heat Transfer
  • Heat Transfer Coefficients
  • Layers
  • Mach Number
  • Skin Friction
  • Turbulent Boundary Layer
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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