A Collection of Data from Test of Full-Scale Missiles to Define Plume Influence on Aerodynamics.

Abstract

Data obtained during a series of tests to determine plume influence on the aerodynamics of a typical high thrust missile are presented. Pressure measurements were obtained over the rear surface of the missile as the sled carried it through the Mach number range of 0.8 to 1.6 as the motor was fired. Portions of these data are influenced by flow disturbances emanated from the carrier sled, other portions are free of this effect. A separate report referenced herein discusses the interference free data. This complete compilation of the data is offered to allow extraction of the meaningful information present in this unique investigation. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1980
Accession Number
ADA127274

Entities

People

  • T. A. Martin

Organizations

  • United States Army Aviation and Missile Command

Tags

DTIC Thesaurus Topics

  • Aerodynamics
  • Air Flow
  • Air Force
  • Air Force Facilities
  • Base Pressure
  • Chambers
  • Coefficients
  • Combustion Chambers
  • Diameters
  • Dynamic Pressure
  • Flow
  • Mach Number
  • Photographs
  • Plastic Explosives
  • Pressure Measurement
  • Simulations
  • Three Dimensional

Readers

  • Explosive Engineering.
  • Fluid Dynamics.
  • Theoretical Analysis.