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Global stability analysis of compressible flow around swept wings
Abstract : The global linear stability of compressible flow in the leading-edge region of a swept wing is studied using an iterative eigenvalue method. This method was implemented via a Jacobian-free framework where direct numerical simulations provide computed flow fields as the required input. It has been found that the investigated leading-edge flow is, over a selected range of flow parameters, most unstable to instabilities of the crossflow type. Our results further confirm that convex leading-edge curvature has a stabilizing influence on this flow. © 2010 Springer-Verlag Berlin Heidelberg.
https://hal-polytechnique.archives-ouvertes.fr/hal-01020666
Contributor : Denis Roura <>
Submitted on : Tuesday, July 8, 2014 - 9:11:59 PM
Last modification on : Monday, September 28, 2020 - 2:14:06 PM
Contributor : Denis Roura <>
Submitted on : Tuesday, July 8, 2014 - 9:11:59 PM
Last modification on : Monday, September 28, 2020 - 2:14:06 PM
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