A viscous shock-layer analysis of 2-D and axisymmetric flows

Author:

GUPTA ROOP1,LEE KAM-PUI2,ZOBY ERNEST1

Affiliation:

1. NASA, Langley Research Center, Hampton, VA

2. Vigyan, Inc., Hampton, VA

Publisher

American Institute of Aeronautics and Astronautics

Reference19 articles.

1. The numerical method used forsolvingthe 2-0VSL equationsisthe same asthat employed foraxisymmetric b d i e s . However,the shock standoffdlstancensh ataspecifiedbody station. m. isobtained from the integration ofEq. (1) where

2. The Vigneron condition 3 isirsed for the pressure gradient in the streamwise momenttoil equation in the subsonic nose region. Theglolxil iteratlons areemployed In this region to upd;iit. the pressure (andshockshape). In the supersixik flowregion, the pressure gradlent term is approximated with a two-point backward differenceand apredlctoi-correctorapproacli:',iii used for the shockshape tomarch the solutio,^ downstream. It should be mentioned here th:tl unlike the axisymmetric calculations 3-6 convergedresults cannot be obtained for the :i 11 shape without the use ofvigneron condition.

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