Direct Numerical Simulation of Receptivity to Roughness in a Swept-Wing Boundary Layer at High Reynolds Numbers
Direct numerical simulations (DNS) are performed to examine the receptivity to roughness in a spatially developing three-dimensional boundary layer over an infinite-swept natural-laminar-flow wing at a freestream Mach number of 0.75 and a chord Reynolds number of approximately 25 million based on the long, swept chord. Stationary crossflow disturbances are excited by applying either critically spaced discrete cylinders of micron size or naturally occurring distributed roughness in the leading-edge region. The DNS data show that the spanwise spectral content of the excited crossflow disturbances is highly dependent upon the shape of roughness elements, and the initial growth of the crossflow structures is a nonlinear function of the element height. The linear growth rate of the excited crossflow disturbances predicted by DNS shows good agreement with linear parabolized stability equations. The receptivity study lays the foundation for investigating the stabilization of the naturally most unstable steady crossflow mode by using spanwise periodic DREs.
G. Nicholson et al., "Direct Numerical Simulation of Receptivity to Roughness in a Swept-Wing Boundary Layer at High Reynolds Numbers," Proceedings of the 48th Fluid Dynamics Conference (2018, Atlanta, GA), American Institute of Aeronautics and Astronautics (AIAA), Jun 2018.
The definitive version is available at https://doi.org/10.2514/6.2018-3076
48th AIAA Fluid Dynamics Conference, 2018 (2018: Jun. 25-29, Atlanta, GA)
Mechanical and Aerospace Engineering
Keywords and Phrases
Direct numerical simulation; Laminar boundary layer; Laminar flow; Numerical models; Reynolds number, Freestream mach number; High Reynolds number; Natural laminar flows; Naturally occurring; Nonlinear functions; Parabolized stability equations; Swept-wing boundary layers; Three-dimensional boundary layers, Swept wings
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2018 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jun 2018