Aerodynamic Test and Analysis of a Slender Generic Missile Configuration

Abstract

This paper discusses the aerodynamic predictions, test , and analyses of a slender fin stabilized missile configuration at Mach numbers from 1.0 to 5. 0. Prediction techniques consisted of both empirical and analytical methods, including state-of-the-art computational fluid dynamic codes. Free flight tests were also conducted on subscale models to obtain an aerodynamic baseline to which the various predictions could be compared. This paper summarizes these results, attempts to identify the physics governing the flight trajectories, and proposes new ideas for further research in this technology area. Keywords: Free flight aerodynamics; Computational Fluid Dynamics; Supersonic; Static Dynamic Stability.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1989
Accession Number
ADA212522

Entities

People

  • G. L. Winchenbach
  • John R. Cipolla
  • Mark A. Fische
  • Roger S. Gates

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Angular Motion
  • Boundary Layer
  • Center Of Gravity
  • Computational Fluid Dynamics
  • Computational Science
  • Computations
  • Experimental Data
  • Flight
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Flight
  • Mach Number
  • Research Facilities
  • Test Facilities
  • Trajectories

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow