J.M.F. Peter, M.J. Kloker

The supersonic flow in a conical nozzle with circular cross section is analyzed using RANS simulations to yield the boundary conditions for planned DNS of film cooling. A simplified one-species approach with calorically perfect gas assumption is used for the gaseous H2O flow, and the results are compared to the experimental data of subproject A2, RWTH Aachen, of the collaborative research center SFB-TRR40. The influence of the wall temperature condition (adiabatic or isothermal with very low wall temperature) on the boundary layer at the cooling-slot position is investigated and the boundary-layer data at the cooling position are extracted. As a reference case the DNS of a fully turbulent boundary layer over a flat plate at Mach number 3.3 with zero pressure gradient and adiabatic wall is shown.

Deutscher Luft- und Raumfahrtkongress 2017, München

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2017

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

urn:nbn:de:101:1-201710202849

CFD, TR40

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20.10.2017