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• W2134718086 abstract "A high fidelity transition prediction methodology has been applied to a swept airfoil design at a Mach number of 0.75 and chord Reynolds number of approximately 17 million, with the dual goal of an assessment of the design for the implementation and testing of roughness based crossflow transition control and continued maturation of such methodology in the context of realistic aerodynamic configurations. Roughness based transition control involves controlled seeding of suitable, subdominant crossflow modes in order to weaken the growth of naturally occurring, linearly more unstable instability modes via a nonlinear modification of the mean boundary layer profiles. Therefore, a synthesis of receptivity, linear and nonlinear growth of crossflow disturbances, and high-frequency secondary instabilities becomes desirable to model this form of control. Because experimental data is currently unavailable for passive crossflow transition control for such high Reynolds number configurations, a holistic computational approach is used to assess the feasibility of roughness based control methodology. Potential challenges inherent to this control application as well as associated difficulties in modeling this form of control in a computational setting are highlighted. At high Reynolds numbers, a broad spectrum of stationary crossflow disturbances amplify and, while it may be possible to control a specific target mode using Discrete Roughness Elements (DREs), nonlinear interaction between the control and target modes may yield strong amplification of the difference mode that could have an adverse impact on the transition delay using spanwise periodic roughness elements. Nomenclature Ainit = initial amplitude of crossflow instability mode or secondary instability mode C, c = wing chord length measured in direction perpendicular to leading edge f = frequency of instability oscillations M = freestream Mach number N = N-factor of linear crossflow instability or secondary instability Re c = Reynolds number based on wing chord X, x = chordwise coordinate in direction perpendicular to leading edge Y = wall-normal coordinate Z = spanwise coordinate in direction parallel to leading edge Λ = wing sweep angle λ = spanwise wavelength of crossflow instability in millimeters in direction parallel to leading edge" @default.
• W2134718086 created "2016-06-24" @default.
• W2134718086 creator A5005228021 @default.
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• W2134718086 date "2010-06-28" @default.
• W2134718086 modified "2023-10-18" @default.
• W2134718086 title "Roughness Based Crossflow Transition Control for a Swept Airfoil Design Relevant to Subsonic Transports" @default.
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• W2134718086 hasPublicationYear "2010" @default.
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