Experimental Investigation of Shock Wave-Boundary Layer Interaction on a Generic Oscillating Bump
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
The presented research investigates the effects of shock wave boundary layer interaction on the unsteady pressure response of the surface of an oscillating structure. A simplified structure, a 2D prismatic bump, located in a straight channel is used to better understand the bending flutter phenomenon. Time-resolved measurements of the unsteady surface pressures and the instantaneous model geometry measurements are performed in order to study the effect of the shock wave on the aerodynamic load acting over the flexible generic bump. The bump is oscillated in a controlled manner with amplitude of ±0.5mm for four reduced frequencies ranging from k=0.123 to k=0.492. The experiments are performed for a transonic flow operating point characterized by an inlet Mach number of 0.69 and a total inlet pressure of 160 kPa, with an outlet Mach number and outlet static pressure of 0.79 and 106 kPa, respectively. The unsteady pressure measurements were performed using recessed mounted pressure transducers with Kulite fast response sensors. The presented results demonstrate that the shock wave induces a strong amplification of the unsteady pressure at the foot of the shock. This amplification was shown to decrease with the increase in reduced frequency, specifically between k=0.123 and k=0.246.
Place, publisher, year, edition, pages
2014. , 66 p.
shock wave, boundary layer, fluid structure interaction, aeroelasticity
IdentifiersURN: urn:nbn:se:kth:diva-156059OAI: oai:DiVA.org:kth-156059DiVA: diva2:764348
Master of Science - Turbomachinery Aeromechanic University Training