Abstract
Paper explores the feasibility of using the shock tube in studying the heat transfer in a compressible turbulent boundary layer with mass injection. It aims to gain further understanding of the film cooling in the compressible flow regime. The test model is a flat plate equipped with a 2D 30° injection slot. Air is used for both driver and driven gases. The injection flow is measured by using the slot as a flow measuring device. Heat transfer data are obtained with thin-film heat gauges. The shock-induced flow has Mach number 0.9, Reynolds number 4.62×l07 per meter, and gas to wall temperature ratio 1.6. The resulting heat transfer measurements are correlated using the scaling parameter suggested by Forth et al. and compared with that of Metzger et al. (1968, 1971)(at Mach 0.03) and Forth et al. (1986) (at Mach 0.55). This comparison revealed a possible Mach number effect on film cooling that has never been addressed before. We use the Prandtl-Glauert formula to model this effect. The agreement is good within measurement uncertainty.
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© 1995 Springer-Verlag Berlin Heidelberg
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Liaw, JY., Bershader, D. (1995). Shock Tube Application to the Study of Compressible Turbulent Boundary Layer with Mass Injection. In: Brun, R., Dumitrescu, L.Z. (eds) Shock Waves @ Marseille I. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-78829-1_16
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DOI: https://doi.org/10.1007/978-3-642-78829-1_16
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