AIAA-1990-603-194 - AlAA 90-0603 Euler Computations of...

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AlAA 90-0603 Euler Computations of Hypersonic Flow with Strong Blowing N. Carter and B. van Leer Univ. of Michigan Ann Arbor, MI 28th Aerospace Sciences Meeting January 8-1 1, 1990/Reno, Nevada For permission to copy or republish, contact the American Institute of Aeronautics and Astronautics 370 L’Enfant Promenade, S.W., Washington, D.C. 20024
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AIAA-90-0603 4’ Euler Computations of Hypersonic Flow with Strong Blowing Nelson Carter * Bram van Leer t The University of Michigan Department of Aerospace Engineering Ann Arbor, MI 48109-2146 Abstract A validation study is presented for a numerical code which calculates a two-dimensional steady-state solu- tion for inviscid hypersonic flows in the presence of strong surface blowing. A higher-orde: Godunov-type finite-volume approach is used to discretize the inviscid Euler equations. Interface values of the state quanti- ties are reconstructed nsing a monotone interpolation technique suggested by Koren, based on Van Leer’s kappa scheme. The interface fluxes are computed using Roc’s upwind-biased flux-difference splitting technique. The time-differencing algorithms used are a locally im- plicit, linearized Gauss-Seidel itcration scheme and an explicit multi-stage scheme with optimized short-wave damping. The results of the numerical calculations are compared with analytical solutions obtained for strong blowing along a flat plate and a wedge with an inverse- squarc-root injcct,ion-velocity distribution Introduction The reccnt revival of intcrcst in hypersonic vehicles has reiicwcd iutcrest in thc study of hypersonic flow. One suhject of study is the usc of surfacc blowing to infln- encc an external hypersonic flow field. Understanding of tlie interaction between the injectcd gas and the high- spccd oiitcr flow is critical 1.0 applications of blowing in propulsion, surface cooling, and control-force gciiera- t,ion. Erpcrimcnts in hypersonic flows, Iiowcvcr, are difficult to perform; thus a heavy reliancc on computa- tional prcdictions has resulkd. 111 the absence of ex- perimental rcsulk, the only recourse is to validate tlie coniputatioiial codes on the basis of flow cases for which aiialytical solutions exist. This ran hclp to distinguish bctwcen physical and niiuicrical effects in cases where only numerical results arc availahlc. A gcncric prohlcni is t,liat of liypcrsonic flow over a *Gradnatr Research Stodent, Mrrrilrer AIAA tfrolessor, Mernlxr AIAA (‘op!right 6 1990 American lnsliluie Afronautics and Astronautics, Inc. All rights reserved. flat plate with distributed blowing off the surface. The displacement effect of the blowing causes a shock wave to form ahead of the blowing region. If the blowing is of sufficient strength, the boundary layer is blown off this is called “strong blowing”. It results in a viscous free shear layer separating an essentially inviscid rotational blown layer next to the wall from an inviscid shock layer extending from the shear layer to the shock (Figure 1).
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AIAA-1990-603-194 - AlAA 90-0603 Euler Computations of...

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