Summary
Effusion cooling by discrete slits and holes in various laminar zero-pressure-gradient super- and hypersonic boundary layers is investigated using direct numerical simulation. A comparison with experimental data for a Mach 2.67 boundary layer with a cool wall and a spanwise slit shows good agreement. For an adiabatic Mach 6 boundary layer it was found that slits are better than holes due to the lower blowing velocity. Slit blowing causes a destabilisation of 2nd mode disturbances, and a complete stabilisation of 1st modes despite the generated maxima of the spanwise vorticity inside the boundary layer. Hole blowing gives rise to counter-rotating streamwise vortices, with a noticeable laminar-flow destabilisation only for large spanwise hole spacings. For a radiation-adiabatic wall at flight conditions the principal behavior is similar but part of the cooling efficiency is lost because of the decreased radiation of heat.
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Linn, J., Kloker, M.J. (2008). Numerical Investigations of Film Cooling. In: Gülhan, A. (eds) RESPACE – Key Technologies for Reusable Space Systems. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 98. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-77819-6_9
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DOI: https://doi.org/10.1007/978-3-540-77819-6_9
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