Development of the Flow Field in Streamwise Corners at Hypersonic Speeds and Effects of the Corner Flow on Downstream Fitted Flaps

摘要

A description is given of the results obtained from investigations carried out on three different configurations of streamwise corners. The experiments were conducted at a free stream Mach number of M = 8.8 and a Reynolds number of Re/m = 4,566,000 in the hypersonic wind tunnel. The pitot pressure, static pressure and total temperature in the flow field were measured, so that it was possible to determine the essential flow quantities. A semi-empirical analysis drawn up on the basis of known shock relations revealed that the state variables behind curved secondary shocks coincide nearly with the experimental results. The major characteristics of the near to wall flow were both pointed out and explained in the corner by making the wall streamlines visible and by measuring the heat transfer and static pressure at the wall. An approximate correlation was achieved between the calculation and the experiment in the estimation of the influences on the rudder efficiency produced by the corner flows.