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.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 oscillati...
[1]
Karim Mazaheri,et al.
Optimization and analysis of shock wave/boundary layer interaction for drag reduction by Shock Control Bump
,
2015
.
[2]
M. Alam,et al.
A Numerical Study on the Control of Self-Excited Shock Induced Oscillation in Transonic Flow around a Supercritical Airfoil
,
2014
.
[3]
W. Schröder,et al.
On the interaction of shock waves and sound waves in transonic buffet flow
,
2013
.
[4]
Y. Volkan Pehlivanoglu,et al.
Drag minimization using active and passive flow control techniques
,
2012
.
[5]
S. Matsuo,et al.
Effects of condensing moist air on shock induced oscillation around an airfoil in transonic internal flows
,
2012
.
[6]
Peipei Zhang,et al.
Numerical Simulation of Gurney Flap on RAE-2822 Supercritical Airfoil
,
2011
.
[7]
H. Olivier,et al.
Unsteady Wave Phenomena on a Supercritical Airfoil
,
2008
.
[8]
N. Qin,et al.
Numerical study of active shock control for transonic aerodynamics
,
2004
.
[9]
E Stanewsky,et al.
Adaptive wing and flow control technology
,
2001
.
[10]
B.H.K. Lee,et al.
Self-sustained shock oscillations on airfoils at transonic speeds
,
2001
.
[11]
D. Mccormick,et al.
Shock/boundary-layer interaction control with vortex generators and passive cavity
,
1993
.
[12]
T. Breitling,et al.
Computation of transonic viscous flow over airfoils with control by an elastic membrane and comparison with control by passive ventilation
,
1991
.
[13]
Lionel L. Levy,et al.
Experimental and Computational Steady and Unsteady Transonic Flows about a Thick Airfoil
,
1978
.