Preliminary Design Aerodynamic Prediction Methodology for Missiles with Nose Bluntness.

Abstract

A semi-empirical methodology is presented for predicting the axial and normal force coefficients and the center of pressure to include nose bluntness effects for missiles. This methodology includes the transonic and supersonic Mach number regime with angles of attack from 0 to 180 degrees. This methodology correlates well with wind tunnel test data. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1978
Accession Number
ADA073664

Entities

People

  • Carter Dinkeloo
  • Charles W. Ingram
  • David Shida
  • Karlheinz O. W. Ball

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterbodies
  • Agreements
  • Air Flow
  • Air Force
  • Bodies
  • Contracts
  • Cylindrical Bodies
  • Dynamics
  • Experimental Data
  • Fineness Ratio
  • Flow
  • Geometry
  • Mach Number
  • Regression Analysis
  • Reynolds Number
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Modeling and Simulation

Technology Areas

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