Experimental and Numerical Investigations on Integrated Intakes for Agile and Highly Swept Aircraft Configurations

Abstract

An experimental study on the effect of boundary layer ingestion into highly integrated intakes is reviewed. First, a generic intake model that has been specially designed for the tests is introduced. Thereafter, the experimental approach that allows for independently varying Mach and Reynolds number as well as boundary layer thickness and mass flux through the intake, is described. The experiments were performed in the Cryogenic Ludwieg-Tube Göttingen of the German Dutch Wind Tunnels (DNW-KRG). Intake performance is discussed in terms of circumferential distortions and total pressure-recovery at the engine face. In a subsequent numerical study efficiencies of vortex generators are evaluated as a means for improving conditions at the engine face.