Asymmetric Lateral Jet Interaction Studies for a Supersonic Missile: CFD Prediction and Comparison to Force and Moment Measurements,

Abstract

Computational Fluid Dynamics (CFD) predictions are compared with the wind-tunnel tests for a missile consisting of ogive-nose cylindrical body, four wings and four in-lined tail panels at nominal supersonic Mach Nos. 2, 3, 4 and 5 at angles-of-attack ranging from 0 to 35 deg with and without a lateral jet thruster with thrust ratios of 1 and 4. Comparisons also include roll angles that lead to asymmetric missile configuration with the thruster jet. Excellent comparisons of the predicted normal force, side force, pitching moment, yawing moment and rolling moment coefficients with the measured data are shown. CFD computed flow field is then utilized to show that the lateral thruster jet effectiveness diminishes as the jet thruster is gradually rolled towards the windward side of the missile. Flow-physics associated with this phenomenon and possible mechanisms to alleviate this effect is discussed.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1997
Accession Number
ADA329063

Entities

People

  • B. Srivastava

Organizations

  • RTX

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Airframes
  • Computational Fluid Dynamics
  • Control Systems
  • Databases
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Simulations
  • Three Dimensional
  • Viscous Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers