Submissile Aerodynamics during Dispensing,

Abstract

A combined analytical and experimental study was conducted to determine the aerodynamic interference effects of a submissile in the presence of a dispenser missile. The analytical predictions are made using NEAR codes modified for applications to missile systems. A wind tunnel test was conducted to measure the static aerodynamic coefficients of a submissile in the flow field of a dispenser missile at Mach numbers 0.8 and 1.2. The parameters observed to have the greatest effect on the interference aerodynamics are the addition of fins on the submissile, the removal of the dispenser bay covers, the dispenser angle of attack and the submissile pitch angle. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 14, 1981
Accession Number
ADA111778

Entities

People

  • Lajpat R. Utreja
  • Thomas E. Lundy
  • William F. Braddock

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aerodynamics
  • Aircrafts
  • Base Pressure
  • Coefficients
  • Coordinate Systems
  • Data Analysis
  • Diameters
  • Dispensers
  • Engineering
  • Experimental Data
  • Flow
  • Flow Fields
  • Mach Number
  • Plastic Explosives
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Missile Defense Systems.