Summary
Shock-induced boundary layer separation has an important influence on the efficiency of hypersonic inlet systems. A method to reduce the boundary layer separation is the implementation of boundary layer bleed. Results are presented for the use of a planar bleed slot at a generic flat plate model for laminar boundary layer flow at a Mach number of 6. The wind tunnel models and the wind tunnel test procedure are optimized by using computational fluid dynamics. An analytical method to predict the key parameters of the boundary layer bleed is presented. The possible reduction of the boundary layer separation and of the thermal loads on the walls by using bleed is demonstrated by results of wind tunnel tests and favorable design parameters for bleed slots are determined.
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References
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© 1997 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Schulte, D., Henckels, A., Schell, I. (1997). Boundary Layer Bleed in Hypersonic Inlets. In: Körner, H., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics. Notes on Numerical Fluid Mechanics (NNFM), vol 60. Vieweg+Teubner Verlag, Wiesbaden. https://doi.org/10.1007/978-3-322-86573-1_38
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DOI: https://doi.org/10.1007/978-3-322-86573-1_38
Publisher Name: Vieweg+Teubner Verlag, Wiesbaden
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Online ISBN: 978-3-322-86573-1
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