Investigation of Plume Induced Separation on a Full-Size Missile at Supersonic Velocities

Abstract

A large amount of data to determine plume effects have been obtained from various simulation techniques. To provide data for evaluating the adequacy of these simulations, a test utilizing a rocket sled to measure surface pressures on a full-size, live, high thrust rocket at Mach number up to Moo 1.6. Selected portions of the data are presented to show Mach number and thrust level effects.

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Document Details

Document Type
Technical Report
Publication Date
Jun 20, 1980
Accession Number
ADA094742

Entities

People

  • T. A. Martin

Organizations

  • United States Army Aviation and Missile Command

Tags

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Data Acquisition
  • Diameters
  • Flow
  • Flow Separation
  • Mach Number
  • Nozzles
  • Pressure Measurement
  • Rocket Engines
  • Rocket Sleds
  • Rockets
  • Simulations
  • Sled Tests
  • Sleds
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Explosive Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow