Reduced frequency effect on an unsteady compressible boundary layer over an oscillating supercritical airfoil-Reference-Cited by-同舟云学术

Reduced frequency effect on an unsteady compressible boundary layer over an oscillating supercritical airfoil

Published:2014-09-30 Issue:4 Volume:37 Page:1379-1390
ISSN:1678-5878
Container-title:Journal of the Brazilian Society of Mechanical Sciences and Engineering
language:en
Short-container-title:J Braz. Soc. Mech. Sci. Eng.

Author:

Fallahpour N.,Haghiri A. A.,Mani M.

Publisher

Springer Science and Business Media LLC

Subject

Mechanical Engineering,General Engineering,Aerospace Engineering,Automotive Engineering,Industrial and Manufacturing Engineering,Applied Mathematics

Link

http://link.springer.com/content/pdf/10.1007/s40430-014-0245-9.pdf

Reference13 articles.

1. Lee T, Gerontakos P (2004) Investigation of flow over an oscillating airfoil. J Fluid Mech 512:313–341

2. Lee T, Basu S (1998) Measurement of unsteady boundary layer developed on an oscillating airfoil using multiple hot-film sensors. Exp Fluids 25(2):108–117

3. Meijering A, Schroder W (2001) Experimental analysis of separated transitional transonic airfoil flow. AIAA 2001–2987

4. Hausmann F, Schroder W (2006) Coated hot-film sensors for transition detection in cruise flight. J Aircr 43(2):456–465

5. Moes TR (1997) Flight demonstration of a shock location sensor using constant voltage hot-film anemometry. NASA Technical Memorandum, Hampton, p 4806

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1. Experimental and Numerical Study of the Unsteady Wake of a Supercritical Airfoil in a Compressible Flow;Journal of Aerospace Technology and Management;2018-12-12

2. Experimental and numerical investigation into the wake of a supercritical airfoil in a compressible unsteady flow;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2016-08-06