Numerical Computation of Hypersonic Viscous Flow over a Sharp Leading Edge

AIAA Journal ◽  
1974 ◽  
Vol 12 (2) ◽  
pp. 129-130 ◽  
Author(s):  
J. C. TANNEHILL ◽  
R. A. MOHLING ◽  
J. V. RAKICH
Keyword(s):  
Viscous Flow ◽  
Numerical Computation ◽  
Leading Edge ◽  
Sharp Leading Edge

Hypersonic viscous flow near a sharp leading edge

AIAA Journal ◽  
1964 ◽  
Vol 2 (9) ◽  
pp. 1660-1661 ◽  
Author(s):  
RICHARD W. GARVINE
Keyword(s):  
Viscous Flow ◽  
Leading Edge ◽  
Sharp Leading Edge

RAREFIED VISCOUS FLOW NEAR A SHARP LEADING EDGE

AIAA Journal ◽  
1963 ◽  
Vol 1 (4) ◽  
pp. 956-958 ◽  
Author(s):  
EDGAR BENDOR
Keyword(s):  
Viscous Flow ◽  
Leading Edge ◽  
Sharp Leading Edge

Application Of Elastic Layers To Register Pressure Field On The Model Surface In Supersonic Flow

2016 ◽  
Vol 11 (1) ◽  
pp. 23-33
Author(s):  
Maxim Golubev ◽  
Andrey Shmakov
Keyword(s):  
Surface Waves ◽  
High Frequency ◽  
High Speed ◽  
Pressure Pulsation ◽  
Pressure Field ◽  
Leading Edge ◽  
Supersonic Wind Tunnel ◽  
Register Pressure ◽  
Elastic Layers ◽  
Sharp Leading Edge

The work presents the results of application of panoramic interferential technique which is based on elastic layers (sensors) usage to obtain pressure distribution on the flat plate having sharp leading edge. Experiments were done in supersonic wind tunnel at Mach number M = 4. Sensitivity and response time are shown to be enough to register pressure pulsation against standing and traveling sensor surface waves. Applying high-frequency image acquiring is demonstrated to make possible to distinguish at visualization images high-speed disturbances propagating in the boundary layer from low-speed surface waves

scholarly journals Numerical Simulation of 3D Viscous Flow in a Linear Compressor Cascade With Tip Clearance

1994 ◽  
Author(s):  
Shun Kang ◽  
Charles Hirsch
Keyword(s):  
Viscous Flow ◽  
Flow Structure ◽  
Leading Edge ◽  
Secondary Flows ◽  
Tip Clearance ◽  
Flow Coefficient ◽  
Compressor Cascade ◽  
Tip Leakage Flow ◽  
Linear Compressor ◽  
Linear Compressor Cascade

A Navier-Stokes solver is applied to investigate the 3D viscous flow in a low speed linear compressor cascade with tip clearance at design and off-design conditions with two different meshes. The algebraic turbulence model of Baldwin-Lomax is used for closure. Relative motion between the blades and wall is simulated for one flow coefficient. Comparisons with experimental data, including flow structure, static and total pressures, velocity profiles, secondary flows and vorticity, are presented for the stationary wall case. It is shown that the code predicts well the flow structure observed in experiments and shows the details of the tip leakage flow and the leading edge horseshoe vortex.

Flow in the initial segment of a tube with a sharp leading edge

1989 ◽  
Vol 56 (2) ◽  
pp. 140-143 ◽  
Author(s):  
V. M. Legkii ◽  
V. A. Rogachev
Keyword(s):  
Initial Segment ◽  
Leading Edge ◽  
Sharp Leading Edge
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