Some Aerodynamic Performance Calculations on Missile Configurations.

Abstract

Axisymmetric bodies with a clean configuration have a rather flat pressure distribution on the cylindrical portion of the body. In this report, axisymmetric bodies with surface cut outs are modelled using an inviscid flow approach with experimental flow results. Literature is available on numerical schemes for aerodynamic calculations on fins at moderately high angles of attack. Fin-body combinations are studied using a nose vortex model and some results reported. Also studied is the asymmetric nose vortex problem on an axisymmetric body at higher angles of attack. This has been studied for conical and ogive forebodies using a modified Wardlow's method. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 31, 1979
Accession Number
ADA070433

Entities

People

  • Jingen Wu
  • K. Suryanarayanan
  • N. Uchiyama
  • R. P. Mikkilineni
  • T. H. Moulden

Organizations

  • University of Tennessee Space Institute

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Axisymmetric
  • Bodies
  • Boundary Layer
  • Cross Flow
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • High Angles
  • Hydrodynamics
  • Inviscid Flow
  • Pressure Distribution
  • Slender Bodies
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.