Lateral Jet Effectiveness Studies for a Missile Using Navier-Stokes Solutions,

Abstract

Several 3-D, viscous, turbulent Navier-Stokes computations have been performed for a missile equipped with and without divert jet thruster for three different wing planforms (having a fixed tail configuration) at a nominal flow Mach number of 3.94, angles-of-attack ranging from 2 to 25 deg and jet trust ratios of one and four. Results are presented to show that the normal force and pitching moment coefficients for all computed cases are predicted within 5 percent of the wind-tunnel data. Synthesis of all the results show low amplification factor for all windward jet thruster cases. For this case the upstream favorable pressure zone created by the windward jet is insufficient to compensate for the massive unfavorable pressure loss on the windward wings/tails due to the jet blockage and jet wrap-around effects.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1996
Accession Number
ADA319941

Entities

People

  • B. Srivastava

Organizations

  • RTX

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautics
  • Airframes
  • Astronautics
  • Computational Fluid Dynamics
  • Dynamic Pressure
  • Experimental Data
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • High Pressure
  • Mach Number
  • Orientation (Direction)
  • Simulations
  • Supersonic Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Propulsion Engineering.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers