Boundary layer transition (BLT) can cause a sharp rise in heat flux and skin friction, which
can seriously affect the flight performance and safety of hypersonic flight vehicles. Therefore …

Control of laminar-to-turbulent transition on a swept-wing is achieved by base-flow
modification in an experimental framework, up to a chord Reynolds number of 2.5 million …

Due to the high sensitivity of laminar wings to uncertain factors, although there have been a
lot of engineering application attempts, so far laminar flow technology has not been …

View Video Presentation: https://doi. org/10.2514/6.2021-2848. vid The linear disturbance
development of cross-flow instability for compressible flows on infinite span swept wings …

Extensive combined experimental and theoretical investigations of the linear evolution of
unsteady (in general) Cross-Flow (CF) and three-dimensional (3D) Tollmien-Schlichting …

Application of ring-type plasma actuators for control of laminar–turbulent transition in a
swept-wing boundary layer is investigated thorough direct numerical simulations. These …

The present work experimentally investigates two forcing strategies toward controlling
stationary crossflow instability (CFI) induced transition manifesting on a swept wing at …

Abstract The Temperature-Sensitive Paint (TSP) method is used for surface-based flow
visualizations on a swept-wing wind-tunnel model with a generic natural laminar-flow airfoil …

Non-parallelism, ie the effect of the slow variation of the boundary-layer flow in the
chordwise and spanwise directions, in general produces a higher-order correction to the …

The use of static or dynamic roughness elements has been shown in the past to delay the
separation of a laminar boundary layer from a solid surface. Here, we examine analytically …