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Numerical Stall Behavior Investigation of an Aircraft Equipped with Coanda Flap and Droop Nose Read chapter Read first chapter

2016 | OriginalPaper | Chapter

Receptivity of a Swept-Wing Boundary Layer to Steady Vortical Free-Stream Disturbances

Authors : Holger B. E. Kurz, Markus J. Kloker

Published in: New Results in Numerical and Experimental Fluid Mechanics X

Publisher: Springer International Publishing

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Abstract

Direct numerical simulations (DNS) of steady vortical free-stream disturbances impinging on the leading edge of a swept wing are performed for a low- and a high-speed subsonic case at a Mach number of 0.16 and 0.65, respectively. The receptivity of the crossflow-instability dominated boundary layer downstream of the stagnation line to the forced disturbances is investigated. The introduced (spanwise) wavelengths are in the order of the most amplified steady crossflow mode in the low Mach-number case and induce respective low-amplitude disturbances in the boundary layer.

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previous chapter Combined Active Separation Control on the Leading Edge and on the Trailing Edge Flap of a Slatless High-Lift Configuration
next chapter Discrete Adjoint Based Optimal Active Control of Separation on a Realistic High-Lift Configuration
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Metadata
Title
Receptivity of a Swept-Wing Boundary Layer to Steady Vortical Free-Stream Disturbances
Authors
Holger B. E. Kurz
Markus J. Kloker
Copyright Year
2016
Book
New Results in Numerical and Experimental Fluid Mechanics X

Print ISBN: 978-3-319-27278-8

Electronic ISBN: 978-3-319-27279-5

Copyright Year: 2016

DOI
https://doi.org/10.1007/978-3-319-27279-5_20

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