An Experimental and Numerical Investigation of Rectangular Embedded Jet Exhausts

Sonic fatigue is present in embedded jet exhaust systems of military aircraft due to the combination of supersonic exhaust velocities and the proximity of the exhaust to the aircraft fuselage. The source of this fatigue is due in part to shock turbulent boundary layer interaction (STBLI) and its characteristics need to be predicted early in the design of the aircraft. The goal of the present study is to improve the understanding of the physical mechanisms involved in shock turbulent boundary layer interaction in rectangular embedded jet exhausts. Model experiments are performed and the measurements used to assess steady and unsteady CFD predictions.