S. Hayböck, H. Abdellah, C. Breitsamter

Innovative nacelle designs and disruptive technologies are required to minimize drag and weight penalties of high bypass ratio turbofan engines. Active flow control can improve flow quality at the aerodynamic interface plane while significantly reducing structural weight and drag through more aggressive, i.e., shorter inlet geometries. In this work, the design of an active flow control system on a future wind tunnel model is numerically investigated. Unsteady Reynolds-Averaged Navier-Stokes simulations are conducted at an angle of attack of [alpha] = 29° and a free-stream Mach number of Ma[alpha] = 0.15. In this initial design phase, blowing is performed steadily with constant mass flow. Possible interactions between the fan and the inlet flow are neglected. Thus, the nacelle is modeled as a generic flow-through nacelle. A sensitivity analysis evaluates the effects of predefined design parameters of the system on inlet performance, starting from a baseline configuration of the active flow control system. Stepwise optimization of parameters significantly improves inlet-specific flow homogeneity coefficients DC60 and SC60 by up to 26.3% and 18.2%, respectively. Further, a flow field analysis reveals that, given a proper choice of parameters, counter-rotating pairs of vortices form downstream of the blowing ports, improving inlet performance considerably.

Deutscher Luft- und Raumfahrtkongress 2023, Stuttgart

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

urn:nbn:de:101:1-2023102012373650287104

10.25967/610087

active flow control, short intake, nacelle aerodynamics

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Hayböck, S.; Abdellah, H.; Breitsamter, C. (2023): A Numerical Design Study for Active Flow Control on Inlets of UHBR Engine Nacelles. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/610087. urn:nbn:de:101:1-2023102012373650287104.

20.10.2023