A Method for Determining the Aerodynamic Characteristics of Two- and Three-Dimensional Shapes at Hypersonic Speeds

Abstract

A method is developed for calculating the pressures on aerodynamic shapes at very high supersonic speeds in dense air with the ratio of specific heats equal to 1. The method is applicable to any body of revolution at zero angle of attack and to any two-dimensional profile. The results of the present paper are compared with previous work of von Karman Epstein on this problem and the differences explained. Some aerodynamic characteristics of several shapes are calculated, and the lift and drag coefficients are shown to be dependent upon the thickness ratio, thickness distribution, and angle of attack.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1948
Accession Number
ADA380705

Entities

People

  • E. B. Klunker
  • Edward N. Bowen
  • H. R. Ivey

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Air Masses
  • Bodies
  • Boundary Layer
  • Centrifugal Force
  • Coefficients
  • Dynamic Pressure
  • Equations
  • Fineness Ratio
  • Flow
  • Heat Energy
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow