Numerical study of transonic shock buffet control over a supercritical airfoil

Yuichi Kuya; Kenshiro Boda; Keisuke Sawada

doi:10.2514/1.C035902

Numerical study of transonic shock buffet control over a supercritical airfoil

Yuichi Kuya, Kenshiro Boda, Keisuke Sawada

ENG - Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

A study conducts unsteady Reynolds-averaged Navier–Stokes (URANS) computation of shock buffet control, using solid vortex generators (VGs). Previous studies mainly focused on how much VGs reduce the size of the shock-induced separation. It discusses how the shock-induced separation changes the effective camber of an airfoil when VGs are adopted, in order to provide further understanding of the flow physics of shock buffet and its control. The numerical results are carefully validated with existing experimental data. The convective numerical fluxes are evaluated by SLAU and a second-order U-MUSCL scheme is employed. The viscous numerical fluxes are evaluated by the second-order central discretization. A correction method proposed by Thornber and team is applied to give the minimum dissipation for low Mach number flow features

Original language	English
Pages (from-to)	1242-1251
Number of pages	10
Journal	Journal of Aircraft
Volume	57
Issue number	6
DOIs	https://doi.org/10.2514/1.C035902
Publication status	Published - 2020

ASJC Scopus subject areas

Aerospace Engineering

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title = "Numerical study of transonic shock buffet control over a supercritical airfoil",

abstract = "A study conducts unsteady Reynolds-averaged Navier–Stokes (URANS) computation of shock buffet control, using solid vortex generators (VGs). Previous studies mainly focused on how much VGs reduce the size of the shock-induced separation. It discusses how the shock-induced separation changes the effective camber of an airfoil when VGs are adopted, in order to provide further understanding of the flow physics of shock buffet and its control. The numerical results are carefully validated with existing experimental data. The convective numerical fluxes are evaluated by SLAU and a second-order U-MUSCL scheme is employed. The viscous numerical fluxes are evaluated by the second-order central discretization. A correction method proposed by Thornber and team is applied to give the minimum dissipation for low Mach number flow features",

author = "Yuichi Kuya and Kenshiro Boda and Keisuke Sawada",

note = "Funding Information: The authors would like to thank Kouchi for providing experimental data. The computations were performed on PRIMERGY CX2550 M4 at the Institute of Fluid Science of Tohoku University.",

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T1 - Numerical study of transonic shock buffet control over a supercritical airfoil

AU - Kuya, Yuichi

AU - Boda, Kenshiro

AU - Sawada, Keisuke

N1 - Funding Information: The authors would like to thank Kouchi for providing experimental data. The computations were performed on PRIMERGY CX2550 M4 at the Institute of Fluid Science of Tohoku University.

PY - 2020

Y1 - 2020

N2 - A study conducts unsteady Reynolds-averaged Navier–Stokes (URANS) computation of shock buffet control, using solid vortex generators (VGs). Previous studies mainly focused on how much VGs reduce the size of the shock-induced separation. It discusses how the shock-induced separation changes the effective camber of an airfoil when VGs are adopted, in order to provide further understanding of the flow physics of shock buffet and its control. The numerical results are carefully validated with existing experimental data. The convective numerical fluxes are evaluated by SLAU and a second-order U-MUSCL scheme is employed. The viscous numerical fluxes are evaluated by the second-order central discretization. A correction method proposed by Thornber and team is applied to give the minimum dissipation for low Mach number flow features

AB - A study conducts unsteady Reynolds-averaged Navier–Stokes (URANS) computation of shock buffet control, using solid vortex generators (VGs). Previous studies mainly focused on how much VGs reduce the size of the shock-induced separation. It discusses how the shock-induced separation changes the effective camber of an airfoil when VGs are adopted, in order to provide further understanding of the flow physics of shock buffet and its control. The numerical results are carefully validated with existing experimental data. The convective numerical fluxes are evaluated by SLAU and a second-order U-MUSCL scheme is employed. The viscous numerical fluxes are evaluated by the second-order central discretization. A correction method proposed by Thornber and team is applied to give the minimum dissipation for low Mach number flow features

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Numerical study of transonic shock buffet control over a supercritical airfoil

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