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Interaction between a normal shock wave and a turbulent boundary layer at high transonic speeds. Part I: Pressure distribution

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Summary

Asymptotic solutions are derived for the pressure distribution in the interaction of a weak normal shock wave with a turbulent boundary layer. The undisturbed boundary layer is characterized by the law of the wall and the law of the wake for compressible flow. In the limiting case considered, for ‘high’ transonic speeds, the sonic line is very close to the wall. Comparisons with experiment are shown, with corrections included for the effect of longitudinal wall curvature and for the boundary-layer displacement effect in a circular pipe.

Zusammenfassung

Asymptotische Lösungen für den Druckverlauf bei der Wechselwirkung zwischen einem schwachen normalen Stoss und einer turbulente Grenzschicht werden hergeleitet. Das Wandgesetz und Geschwindigkeitsdefekt-Gesetz für kompressible Strömung kennzeichnen die ungestörte Grenzschicht. Der Grenzfall hoher transsonischen Strömung, in dem die Schallinie in der Nähe der Wand liegt, wird untersucht. Die theoretischen Ergebnisse werden mit Experimenten verglichen. Dabei wird die Wandkrümmung und im Fall der Rohrströmung die Verdrängungsdicke berücksichtigt.

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  1. Dept of Aerospace Engineering, The University of Michigan, Ann Arbor, Michigan, USA

    A. F. Messiter

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Messiter, A.F. Interaction between a normal shock wave and a turbulent boundary layer at high transonic speeds. Part I: Pressure distribution. Journal of Applied Mathematics and Physics (ZAMP) 31, 204–226 (1980). https://doi.org/10.1007/BF01590748

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