HYPERSONIC FLOWFIELD AND HEAT FLUX PECULIARITIES ON THE NEW SPACE LAUNCHER WITH WINGED REUSABLE FIRST STAGE.

摘要

The main purpose of this work is to investigate experimentally under hypersonic velocities the features of the flow field structure and the heat flux distribution on the new space launcher with two attached winged modules and on the separated winged module of the first stage. It is important to determine regions and elements of vehicle layout subjected to increased aerodynamic and heat loads, to develop methods and means for vehicle layout protection against the loads obtained. The following investigations are performed in the experiments at TsAGI wind tunnels T-117 and UT-1M: investigations of surface heat flux by means of thermo sensitive coatings (melting paints) at T-117; investigations of surface heat flux by TSP-method (temperature sensitive paint - luminophor) at UT-1M and schlieren flow visualization.