Accession Number : ADA319941

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

Corporate Author : RAYTHEON CO TEWKSBURY MA ELECTRONIC SYSTEMS DIV

Personal Author(s) : Srivastava, B.

PDF Url : ADA319941

Report Date : SEP 1996

Pagination or Media Count : 47

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.

Descriptors :   *WING BODY CONFIGURATIONS, *JET FLOW, GUIDED MISSILES, PITCH(MOTION), TURBULENCE, TURBULENT FLOW, COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, AERODYNAMIC FORCES, WIND TUNNEL TESTS, MACH NUMBER, NAVIER STOKES EQUATIONS, VISCOUS FLOW, THRUSTERS, THREE DIMENSIONAL FLOW.

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

Distribution Statement : APPROVED FOR PUBLIC RELEASE