Towards transition modelling for supersonic laminar flow control based on spanwise periodic roughness elements.

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2005
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Abstract
Laminar flow control (LFC) is one of the key enabling technologies for quiet and efficient supersonic aircraft. Recent work at Arizona State University (ASU) has led to a novel concept for passive LFC, which employs distributed leading edge roughness to limit the growth of naturally dominant crossflow instabilities in a swept-wing boundary layer. Predicated on nonlinear modification of the mean boundary-layer flow via controlled receptivity, the ASU concept requires a holistic prediction approach that accounts for all major stages within transition in an integrated manner. As a first step in developing an engineering methodology for the design and optimization of roughness-based supersonic LFC, this paper reports on canonical findings related to receptivity plus linear and nonlinear development of stationary crossflow instabilities on a Mach 2.4, 73 degrees swept airfoil with a chord Reynolds number of 16.3 million.
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choudhari2005towardsphilosophical Use this key to autocite in the manuscript while using SciMatic Manuscript Manager or Thesis Manager
Authors Choudhari, Meelan;Chang, Chau-Lyan;Jiang, Li;
Journal philosophical transactions series a, mathematical, physical, and engineering sciences
Year 2005
DOI
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Keywords
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