TY - JOUR

T1 - Shock wave instability in a bent channel with subsonic/supersonic exit

AU - Kuzmin, Alexander

PY - 2019/1

Y1 - 2019/1

N2 - Two- and three-dimensional turbulent airflows in a 9-degrees-bent channel are studied numerically. The inner surfaces of upper and lower walls are parallel to each other upstream and downstream of the bend section. The free stream is supersonic, whereas the flow at the channel exit is either supersonic or subsonic depending on the given backpressure. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver ANSYS CFX. The solutions reveal instability of formed shock waves and a flow hysteresis in considerable bands of the free-stream Mach number at zero and negative angles of attack. The instability is caused by an interaction of shocks with the expansion flow formed over the convex bend of lower wall.

AB - Two- and three-dimensional turbulent airflows in a 9-degrees-bent channel are studied numerically. The inner surfaces of upper and lower walls are parallel to each other upstream and downstream of the bend section. The free stream is supersonic, whereas the flow at the channel exit is either supersonic or subsonic depending on the given backpressure. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver ANSYS CFX. The solutions reveal instability of formed shock waves and a flow hysteresis in considerable bands of the free-stream Mach number at zero and negative angles of attack. The instability is caused by an interaction of shocks with the expansion flow formed over the convex bend of lower wall.

KW - shock waves

KW - curved channel

KW - instability

KW - hysteresis

KW - turbulent boundary layer

KW - FLOW

U2 - 10.12989/aas.2019.6.1.019

DO - 10.12989/aas.2019.6.1.019

M3 - статья

VL - 6

SP - 19

EP - 30

JO - Advances in Aircraft and Spacecraft Science

JF - Advances in Aircraft and Spacecraft Science

SN - 2287-528X

IS - 1

ER -