MEASUREMENTS WITH THE ELAC-1-CONFIGURATION AT MACH-7

In the present paper experimental results will be given which have bee n achieved in the Aachen shock tunnel TH 2 for the ELAC 1-configuratio n. For this configuration a delta wing with two winglets was chosen to represent the lower stage of a two-stage space transportation system. It has two elliptical half-cross sections, where the geometry is defi ned as simple as possible to allow for an easy numerical treatment of the flow. In this paper some of the experimental results are compared with numerical ones where a good agreement is achieved between both of them. For two flow conditions pressure and heat flux measurements wer e performed for the lower and upper side. Special effort was spent on the simulation of the precompression flow along the windward side and the inlet flow into the engine. For this purpose a two-dimensional air inlet model was mounted on the windward side of ELAC 1. Pressure and heat flux measurements on the centerline along the inlet as well as sc hlieren photographs give evidence about the complex flow structure in this region. Tests have been performed with a conical as well as a con toured wind tunnel nozzle. A comparison of the results achieved allows to estimate the influence of the source flow effect of the conical no zzle.