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- W2462149968 abstract "Transonic flow past a supercritical airfoil is strongly influenced by the interaction of shock wave with boundary layer. This interaction induces unsteady self-sustaining shock wave oscillation, flow instability, drag rise and buffet onset which limit the flight envelop. In the present study, a computational analysis has been carried out to investigate the flow past a supercritical RAE2822 airfoil in transonic speeds. To control the shock wave oscillation, a cavity is introduced on the airfoil surface where shock wave oscillates. Different geometric configurations have been investigated for finding optimum cavity geometry and dimension. Unsteady Reynolds averaged Navier-Stokes equations (RANS) are computed at Mach 0.729 with an angle of attack of 5°. Computed results are well validated with the available experimental data in case of baseline airfoil. However, in case of airfoil with control cavity; it has been observed that the introduction of cavity completely suppresses the unsteady shock wave oscillation. Further, significant drag reduction and successive improvement of aerodynamic performance have been observed in airfoil with shock control cavity." @default.
- W2462149968 created "2016-07-22" @default.
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- W2462149968 date "2016-01-01" @default.
- W2462149968 modified "2023-10-10" @default.
- W2462149968 title "Effect of cavity on shock oscillation in transonic flow over RAE2822 supercritical airfoil" @default.
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- W2462149968 doi "https://doi.org/10.1063/1.4958385" @default.
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