Design of a cone-cylinder-flare configuration for hypersonic boundary-layer stability analyses and measurements with attached and separated flows
Résumé
The stability of hypersonic boundary-layer over axisymmetric cone-cylinder-flare configurations at Mach 6 and zero degree angle of attack is investigated for different Reynolds numbers. The shapes have been specifically designed for wind tunnel test experiments to create well suited geometries for hypersonic laminar-turbulent transition analyses with attached and separated flows taking into account the effects of pressure gradients, flow expansion and recompression, on the hypersonic boundary-layer stability. After a thorough study of the aerodynamic flows obtained in fully laminar conditions on each configuration, linear stability theory (LST) and linear parabolized stability equations (PSE) are used to predict the amplification rates of the boundary-layer disturbances for the case without flow separation. The numerical stability results are compared to wind tunnel measurements obtained in the BAM6QT (Boeing AFOSR Mach-6 Quiet Tunnel) wind tunnel. The semi-empirical eN method allows to correlate transition with the integrated growth of the linear instability waves.
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