AN ENGINEERING METHOD FOR RAPID CALCULATION OF SUPERSONIC-HYPERSONIC PRESSURE DISTRIBUTIONS ON LIFTING AND NON-LIFTING POINTED BODIES OF REVOLUTION AND SEVERAL SPECIAL CASES OF BLUNT-NOSED BODIES OF REVOLUTION

Abstract

The method, which utilized hybrid tandem solutions involving Generalized Newtonian and Shock-Expansion theories, provides accurate results for a variety of nose shapes and fineness ratios over a range of supersonic/ hypersonic Mach numbers. The numerical simplicity of the method, which makes it readily applicable for quick hand-calculational procedures, was the prime factor in its selection and publication. The investigation for lifting bodies indicates the present method is applicable for bodies of revolution at angles of attack up to about ten degrees. The report presents numerical examples showing stepwise calculational procedures for obtaining pressure coefficient and local Mach number distributions along the meridians of a body of revolution at angle of attack.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1965
Accession Number
AD0630342

Entities

People

  • R. J. Vendemia Jr.

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Artificial Intelligence
  • Bodies Of Revolution
  • Boundary Layer
  • Coefficients
  • Engineering
  • Experimental Data
  • Fineness Ratio
  • Fluid Dynamics
  • Lifting Bodies
  • Mach Number
  • Method Of Characteristics
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Gradients
  • Slender Bodies
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow