Investigation of Distributed Roughness Element System Based on Dielectric Barrier Discharge for the Suppression of Stationary Cross-Flow Vortices on the Swept Wing
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Publisher
Springer International Publishing
Link
https://link.springer.com/content/pdf/10.1007/978-3-030-67902-6_12
Reference7 articles.
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2. White, E.B., Saric, W.S.: Application of variable leading-edge roughness for transition control on swept wings. In: 38th Aerospace Sciences Meeting and Exhibit (2000)
3. Chernyshev, S.L., Kuryachii, A.P., Manuilovich, S.V., Rusyanov, D.A., Skvortsov, V.V.: Attenuation of cross-flow-type instability in compressible boundary layer by means of plasma actuators. In: 51st AIAA Aerosp. Sci. Meet. Incl. New Horizons Forum Aerosp. Expo. (2013)
4. Yadala, S., Hehner, M.T., Serpieri, J., Benard, N., Dörr, P.C., Kloker, M.J., Kotsonis, M.: Experimental control of swept-wing transition through base-flow modification by plasma actuators (2018)
5. Grek, G.R., Kozlov, V.V., Titarenko, S.V., Klingmann, B.G.B.: The influence of riblets on a boundary layer with embedded streamwise vortices. Phys. Fluids (1995). https://doi.org/10.1063/1.868694
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