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Outputs (137)

Computational study of flow over generic fan-wing airfoil (2007)
Journal Article
Duddempudi, D., Yao, Y., Edmondson, D., Yao, J., & Curley, A. (2007). Computational study of flow over generic fan-wing airfoil. Aircraft Engineering and Aerospace Technology, 79(3), 238-244. https://doi.org/10.1108/00022660710743831

Purpose - The paper seeks to perform a detailed numerical study of flow over a generic fan-wing airfoil and also attempts to modify the geometry for the improvement of the aerodynamic performance. Design/methodology/approach - Advanced computational... Read More about Computational study of flow over generic fan-wing airfoil.

The effect of Mach number on unstable disturbances in shock/boundary-layer interactions (2007)
Journal Article
Yao, Y., Krishnan, L., Sandham, N. D., & Roberts, G. T. (2007). The effect of Mach number on unstable disturbances in shock/boundary-layer interactions. Physics of Fluids, 19(5), 054104. https://doi.org/10.1063/1.2720831

The effect of Mach number on the growth of unstable disturbances in a boundary layer undergoing a strong interaction with an impinging oblique shock wave is studied by direct numerical simulation and linear stability theory (LST). To reduce the numbe... Read More about The effect of Mach number on unstable disturbances in shock/boundary-layer interactions.

On the response of shock-induced separation bubble to small amplitude disturbances (2005)
Journal Article
Krishnan, L., Yao, Y., Sandham, N. D., & Roberts, G. T. (2005). On the response of shock-induced separation bubble to small amplitude disturbances. Modern Physics Letters B, 19(28-29), 1495-1498. https://doi.org/10.1142/S0217984905009742

Numerical simulations of an oblique shock interacting with a compressible laminar boundary layer are reported. The Mach number ranges from 2 to 6.85, while the Reynolds number based on the distance to the impingement location is fixed at 3 × 105. All... Read More about On the response of shock-induced separation bubble to small amplitude disturbances.

Structure and Energetics of a Turbulent Trailing Edge Flow (2003)
Journal Article
Thomas, T. G., Yao, Y., & Sandham, N. D. (2003). Structure and Energetics of a Turbulent Trailing Edge Flow. Computers and Mathematics with Applications, 46(4), 671-680. https://doi.org/10.1016/S0898-1221%2803%2990024-1

Results from a direct numerical simulation (DNS) of turbulent flow over a rectangular trailing edge geometry are used to study energy transfers in detail. The numerical procedure employs a separate boundary layer simulation which is used to generate... Read More about Structure and Energetics of a Turbulent Trailing Edge Flow.

Simulation and modelling of turbulent trailing-edge flow (2002)
Journal Article
Yao, Y., Savill, A. M., Sandham, N. D., & Dawes, W. N. (2002). Simulation and modelling of turbulent trailing-edge flow. Flow, Turbulence and Combustion, 68(4), 313-333. https://doi.org/10.1023/A%3A1021755327045

Computations of turbulent trailing-edge flow have been carried out at a Reynolds number of 1000 (based on the free-stream quantities and the trailing-edge thickness) using an unsteady 3D Reynolds-Averaged Navier-Stokes (URANS) code, in which two-equa... Read More about Simulation and modelling of turbulent trailing-edge flow.

Direct numerical simulation of turbulent trailing-edge flow with base flow control (2002)
Journal Article
Yao, Y., & Sandham, N. (2002). Direct numerical simulation of turbulent trailing-edge flow with base flow control. AIAA Journal, 40(9), 1708-1716. https://doi.org/10.2514/2.1864

Direct numerical simulation has been carried out for turbulent flow over a rectangular trailing edge at a Reynolds number of 1 × 103 (based on the freestream quantities and the trailing-edge thickness) and ratio of boundary-layer displacement thickne... Read More about Direct numerical simulation of turbulent trailing-edge flow with base flow control.