There is a worldwide-rising interest in scramjet propulsion technique because of its promising performances for hypersonic flight. The US-HyperX43 vehicle achieved flight Mach numbers between 7 and 10, followed by the X51 wave rider which flew six minutes with Mach 5.1.

Hypersonic ground testing of these engines or components of these is still a challenging task because of the extreme hypersonic flow conditions. In the presentation results of an experimental study are shown which has been performed at the shock tunnel TH2 of RWTH Aachen University. Flow phenomena associated with the intake flow have been studied in detail. A simple analytical model will be presented which allows to describe the main effects on shock wave boundary layer interaction caused by leading edge bluntness and varying wall temperature. For this, a heat able intake model has been designed and built which allows wall temperatures up to 1000 K to ensure more realistic conditions. The flow in the engine isolator and associated shock train phenomena have been investigated with the same wind tunnel model. The achieved results demonstrate a strong influence of the wall temperature on the overall flow behaviour which therefore has to be simulated correctly in the experiments as well as in the numerical simulations.

 

1978-1982: Study at University of Technology Aachen, Germany , Master of science, Aerospace Technology

1982-1986: Research scientists at the Shock wave Lab., RWTH Aachen，Dr-ing.(Doctoral Degree)

1986-1996: Delegated to the Shock wave Lab., RWTH Aachen (Employed at Daimler-Benz Aerospace, Airbus GmbH, Bremen, Germany)

1996-now: Head of the Shock wave Lab., RWTH  Aachen,

Professor of High Temperature Gas Dynamics

Inlet of a Scramjet Engine

Cooling Methods for Hypersonic Vehicles

Generation of Nanoparticles in Supersonic Flow

Pressure Waves around an Airfoil

Numerical Investigation of Unsteady Wave Processes

Forming by Use of Gas Detonation

Cold Gas-Coating Technique

Chemically Reactive Hypersonic Flows