An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4.

Abstract

The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1977
Accession Number
ADA040860

Entities

People

  • C. Wayne Dahlke

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aerodynamic Stability
  • Air Force
  • Base Pressure
  • Boundary Layer
  • Dynamic Pressure
  • Engineering
  • Flow
  • Jet Propulsion
  • Layers
  • Mach Number
  • Measurement
  • Mechanical Engineering
  • Physics Laboratories
  • Simulators
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.