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Numerical and Experimental Investigations for Super Sonic Active Flow Control in the Transonic Mach Regime
Citation key 2019_ebert_dlrk
Author Ebert, C. and Mihalyovics, J. and Staats, M. and Peitsch, D. and Weiss, J.
Pages 490165
Year 2019
DOI 10.25967/490165
Location Darmstadt, Germany
Journal Deutscher Luft- und Raumfahrtkongress
Month 10
Note Technische Universität Berlin:
C. Ebert, J. Mihalyovics, M. Staats, D. Peitsch, J. Weiss
Editor Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.
Abstract In the present paper, an experimental investigation on the application of high-speed sweeping jet actuators was carried out. It examines the feasibility of a super sonic exit jet to control boundary layer separation caused by an adverse pressure gradient in a compressible Mach number regime. The first part of the investigation includes a thorough assessment of the used sweeping jet actuator by three dimensional numerical simulations using OpenFoam®. A validation of the results was done by means of schlieren visualization within the actuator and dynamic pressure measurements at the actuator outlet. The outlet signal of the actuator features a characteristic switching frequency of fs ≈ 1200 Hz and a peak Mach number of Ma ≈ 1.4 which was evident in the experiments and the CFD simulation. The supply pressure ratio of the actuator was set to PR = 3.6 using compressed air. The second part of the paper presents the results of the wind tunnel experiments using a test section with the geometry of a half-diffusor ramp equipped with two sweeping jet actuators. Inflow conditions of Mach numbers ranging from Ma∞ = 0.3 to Ma∞ = 0.8 were investigated. The conducted wind tunnel experiments include detailed oil flow surface visualizations and mean surface pressure measurements in order to demonstrate the impact of the active flow control system. By varying the mass flow rate of the actuator system different operating points were studied. The presented results indicate the positive effect of active flow control regarding the pressure rise over the ramp in a compressible Mach number regime. The separated flow region was significantly reduced.
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