Influence of transpiration cooling on second mode instabilities investigated on hypersonic, conical flows

Abstract

In the present study the influence of active cooling on hypersonic boundary layer transition at different Mach numbers, from 7 up to 10, is investigated. The analyses are carried out on a 7° half angle, blunted cone with different nose radii and various gas injection mass flow rates. In all cases low mass fluxes, which do not inducing visible shocks in the schlieren images, are applied. As injection gas nitrogen is used. At the considered free stream conditions second modes are the dominant boundary layer instabilities, which are consequently the focus of this study. The stability analyses are performed by means of the stability code NOLOT, NOnLOcal Transition analysis, of the German Aerospace Center (DLR). The influence of different mass injection on the frequencies and growth rates of the second modes is analyzed in detail. The effect on the transition onset locations are discussed. The numerical predictions are compared with experimental results. The experimental data referred to in the present study were obtained in the DLR High Enthalpy Shock Tunnel Göttingen (HEG).