Development of a Computer Program to Calculate Aerodynamic Characteristics of Bodies and Wing-Body Combinations.

Abstract

A new method has been developed for calculating an approximate surface pressure distribution over axisymmetric bodies, with pointed or blunted noses, at angle of attack in supersonic flow. A modified form of the second-order shock-expansion method is developed and matched to modifed Newtonian theory near the nose. Surface pressure distributions compared well with experimental data on blunted cones with and without flares at Mach numbers from 1.5 to 4.63 and angles of attack to 12 deg. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1978
Accession Number
ADA055846

Entities

People

  • Fred R. Dejarnette
  • Kenneth M. Jones

Organizations

  • North Carolina State University

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Air Force Facilities
  • Arm Bones
  • Artillery
  • Computer Programs
  • Curvature
  • Engineering
  • Fluid Dynamics
  • Geometry
  • Mechanical Engineering
  • Military Research
  • North Carolina
  • Pressure Distribution
  • Pressure Gradients
  • Stagnation Point
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Theoretical Analysis.

Technology Areas

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