The Interaction Between Boundary Layer and Shock Waves in Transonic Flow

1946 ◽  
Vol 13 (12) ◽  
pp. 623-637 ◽  
Author(s):  
HANS WOLFGANG LIEPMANN
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Transonic Flow ◽  
And Shock Waves

Prediction of Viscous Effects in Steady Transonic Flow Past an Aerofoil

1979 ◽  
Vol 30 (3) ◽  
pp. 485-505 ◽  
Author(s):  
M.R. Collyer ◽  
R.C. Lock
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Transonic Flow ◽  
Lift Coefficient ◽  
Inviscid Flow ◽  
Viscous Effects ◽  
Flow Past ◽  
Boundary Layer Development ◽  
Transition Position ◽  
Realistic Representation

SummaryAn account is given of a numerical method for calculating transonic flow past an aerofoil with an allowance for viscous effects, providing that the boundary layer remains fully attached over the aerofoil surface. The method has been developed by combining, in an iterative manner, calculations of the inviscid flow with calculations of the compressible boundary layer and wake. The solution for the inviscid flow is obtained by an iterative scheme, originally established by Garabedian & Korn, which has been modified to give a more realistic representation of shock waves. The boundary-layer development is treated as laminar initially; at a certain transition position a turbulent boundary layer is assumed to develop, and this is determined by the lag-entrainment method of Green et al. Comparisons of the results from the numerical scheme with some experimental measurements are shown for various examples in which shock waves of moderate strength are present. The method predicts, with reasonable accuracy, both the detailed pressure distribution and the variation of drag coefficient with lift coefficient.

Simulation of the Effects of Shock Wave Passing on a Turbine Rotor Blade

1985 ◽  
Vol 107 (4) ◽  
pp. 998-1006 ◽  
Author(s):  
D. J. Doorly ◽  
M. L. G. Oldfield
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Shock Waves ◽  
High Frequency ◽  
Guide Vane ◽  
Turbine Rotor ◽  
Surface Boundary ◽  
Suction Surface ◽  
Very High Frequency ◽  
And Shock Waves

The unsteady effects of shock waves and wakes shed by the nozzle guide vane row on the flow over a downstream turbine rotor have been simulated in a transient cascade tunnel. At conditions representative of engine flow, both wakes and shock waves are shown to cause transient turbulent patches to develop in an otherwise laminar (suction-surface) boundary layer. The simulation technique employed, coupled with very high-frequency heat transfer and pressure measurements, and flow visualization, allowed the transition initiated by isolated wakes and shock waves to be studied in detail. On the profile tested, the comparatively weak shock waves considered do not produce significant effects by direct shock-boundary layer interaction. Instead, the shock initiates a leading edge separation, which subsequently collapses, leaving a turbulent patch that is convected downstream. Effects of combined wake- and shock wave-passing at high frequency are also reported.

Experimental study of heat transfer in the boundary layer of a flat plate with the impact of weak shock waves on the leading edge

2020 ◽  
Author(s):  
V. L. Kocharin ◽  
A. A. Yatskikh ◽  
D. S. Prishchepova ◽  
A. V. Panina ◽  
Yu. G. Yermolaev ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Experimental Study ◽  
Shock Waves ◽  
Flat Plate ◽  
Leading Edge ◽  
Weak Shock ◽  
The Impact

Flow patterns of dual-incident shock waves/turbulent boundary layer interaction

2020 ◽  
Vol 23 (6) ◽  
pp. 931-935
Author(s):  
Xin Li ◽  
Hui-jun Tan ◽  
Yue Zhang ◽  
He-xia Huang ◽  
Yun-jie Guo ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Turbulent Boundary Layer ◽  
Flow Patterns ◽  
Incident Shock ◽  
Layer Interaction ◽  
Boundary Layer Interaction
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