N95 23433

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ABSTRACT:

CFD Flowfield Simulation of Delta Launch Vehicles in a Power-on ConfigurationI"

Workshop for Computational Fluid Dynamic (CFD) Applications in Rocket Propulsion,George C. Marshall Space Flight Center, April 20-22, 1993

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By: D. L. Pavish +, T. P. Gielda*, B. K. Soni **, J. E. Deese ++, and R. K. Agarwal ++

This paper summarizes recent work at McDonnell Douglas Aerospace (MDA) to developand validate computational fluid dynamic (CFD) simulations of under expanded rocketplume external flowfields for multibody expendable launch vehicles (ELVs). Multi-engine reacting gas flowfield predictions of ELV base pressures are needed to definevehicle base drag and base heating rates for sizing external nozzle and base regioninsulation thicknesses. Previous ELV design programs used expensive multibody

power-on wind tunnel tests that employed chamber/nozzle injected high pressure coldor hot-air. Base heating and pressure measurements were belatedly made during thefirst flights of past ELVs to correct estimates from semi-empirical engineering models orscale model tests.

Presently, CFD methods for use in ELV design are being jointly developed at the SpaceTransportation Division (MDA-STD) and New Aircraft Missiles Divison (MDA-NAMD).An explicit three dimensional, zonal, finite-volume, full Navier-Stokes (FNS) solver withfinite rate hydrocarbon/air and aluminum combustion kinetics was developed to

accurately compute ELV power-on flowfields. Mississippi State University's GENIE ++general purpose interactive grid generation code was chosen to create zonal, finitevolume viscous grids. Axisymmetric, time dependent, turbulent CFD simulations of aDelta DSV-2A vehicle with a MB-3 liquid main engine burning RJ-1/LOX were first

completed. Hydrocabon chemical kinetics and a k-E turbulence model were employedand predictions were validated with flight measurements of base pressure andtemperature. Zonal internal/external grids were created for a Delta DSV-2C vehicle witha MB-3 and three Castor-I solid motors burning and a Delta-II with an RS-27 mainengine (LOX/RP-1) and 9 GEMs attached/6 burning. Cold air, time dependent FNScalculations were performed for DSV-2C during 1992. Single phase simulations thatemploy finite rate hyrocarbon and aluminum (solid fuel) combustion chemistry arecurrently in progress. Reliable and efficient Eulerian algorithms are needed to modeltwo phase (solid-gas) momentum and energy transfer mechanisms for solid motor fuelcombustion products.

+ McDonnell Douglas Aerospace-Space Transportation Division, Huntingon Beach,Ca.

++ McDonnell Douglas Aerospace-New Aircraft Missile Products Division, St. Louis, Mo.* Presently at Ford Motor Co., Detroit, Mi.** Mississippi State Univ. NSF/Eng. Research Center, Strarkville, Miss.

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