Accession Number : ADA329063

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

Corporate Author : RAYTHEON CO TEWKSBURY MA ELECTRONIC SYSTEMS DIV

Personal Author(s) : Srivastava, B.

PDF Url : ADA329063

Report Date : 1997

Pagination or Media Count : 34

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.

Descriptors :   *GUIDED MISSILES, *COMPUTATIONAL FLUID DYNAMICS, *WIND TUNNEL TESTS, AERODYNAMIC CONFIGURATIONS, ROLL, PITCH(MOTION), YAW, MOMENTS, ANGLE OF ATTACK, FLOW FIELDS, ASYMMETRY, MACH NUMBER, FLIGHT MANEUVERS, WINGS, AZIMUTH, THRUST CONTROL, DYNAMIC PRESSURE, SUPERSONIC AIRCRAFT.

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE