Application possibilities of laser Doppler anemometry in the investigation of the transonic interaction between shock wave and boundary layer

A laser Doppler anemometer was used in a transonic wind tunnel to investigate the flows about wing profiles containing shock waves and separated zones. Flow states characterized by the absence or the presence of a shock-induced separation were created. The results of the laser anemometry are presented in the form of two-dimensional Mach number distributions. The good agreement with analogous results obtained by classical probe measurements and model calculations indicate that the laser anemometer can be successfully utilized for the quantitative analysis of shock-boundary layer interferences about transonic wing profiles.