Boundary conditions for CFD simulations of supersonic boundary-layer flow through discrete holes

2000 ◽  
Author(s):  
D. Benson ◽  
T. Shih ◽  
D. Davis ◽  
B. Willis
Keyword(s):  
Boundary Layer ◽  
Boundary Conditions ◽  
Boundary Layer Flow ◽  
Supersonic Boundary Layer ◽  
Cfd Simulations ◽  
Flow Through ◽  
Layer Flow

scholarly journals Stability Analysis on Nonequilibrium Supersonic Boundary Layer Flow with Velocity-Slip Boundary Conditions

Fluids ◽  
2019 ◽  
Vol 4 (3) ◽  
pp. 142
Author(s):  
Xin He ◽  
Kai Zhang ◽  
Chunpei Cai
Keyword(s):  
Boundary Layer ◽  
Stability Analysis ◽  
Boundary Conditions ◽  
Boundary Layer Flow ◽  
Velocity Slip ◽  
Linear Stability Theory ◽  
Resonance Phenomenon ◽  
Slip Boundary Conditions ◽  
Slip Boundary ◽  
Layer Flow

This paper presents our recent work on investigating velocity slip boundary conditions’ effects on supersonic flat plate boundary layer flow stability. The velocity-slip boundary conditions are adopted and the flow properties are obtained by solving boundary layer equations. Stability analysis of two such boundary layer flows is performed by using the Linear stability theory. A global method is first utilized to obtain approximate discrete mode values. A local method is then utilized to refine these mode values. All the modes in these two scenarios have been tracked upstream-wisely towards the leading edge and also downstream-wisely. The mode values for the no-slip flows agree well with the corresponding past results in the literature. For flows with slip boundary conditions, a stable and an unstable modes are detected. Mode tracking work is performed and the results illustrate that the resonance phenomenon between the stable and unstable modes is delayed with slip boundary conditions. The enforcement of the slip boundary conditions also shortens the unstable mode region. As to the conventional second mode, flows with slip boundary conditions can be more stable streamwisely when compared with the results for corresponding nonslip flows.

An instability in supersonic boundary-layer flow over a compression ramp

1995 ◽  
Vol 300 ◽  
pp. 265-285 ◽  
Author(s):  
K. W. Cassel ◽  
A. I. Ruban ◽  
J. D. A. Walker
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Flow ◽  
Streamwise Velocity ◽  
Supersonic Boundary Layer ◽  
Recirculation Region ◽  
Hypersonic Boundary Layer ◽  
Recirculating Flow ◽  
Inflection Points ◽  
Compression Ramp ◽  
Layer Flow

Separation of a supersonic boundary layer (or equivalently a hypersonic boundary layer in a region of weak global interaction) near a compression ramp is considered for moderate wall temperatures. For small ramp angles, the flow in the vicinity of the ramp is described by the classical supersonic triple-deck structure governing a local viscous-inviscid interaction. The boundary layer is known to exhibit recirculating flow near the corner once the ramp angle exceeds a certain critical value. Here it is shown that above a second and larger critical ramp angle, the boundary-layer flow develops an instability. The instability appears to be associated with the occurrence of inflection points in the streamwise velocity profiles within the recirculation region and develops as a wave packet which remains stationary near the corner and grows in amplitude with time.

A Theoretical Investigation of Transonic Flows in Radial Compressor Diffusers

1983 ◽  
Vol 105 (3) ◽  
pp. 452-456
Author(s):  
H. O. Jeske ◽  
I. Teipel
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Flow ◽  
Pressure Ratio ◽  
Numerical Procedure ◽  
Vaned Diffuser ◽  
High Pressure Ratio ◽  
Integral Methods ◽  
Boundary Layer Interaction ◽  
Flow Through ◽  
Layer Flow

The transonic flow in a diffuser of a centrifugal compressor with high pressure ratio has been analyzed by a numerical procedure. The method consists of an inviscid calculation of the pressure field in the vaned diffuser and of a determination of the boundary layer flow along the blades. The diffuser has been equipped with curved vanes, and only the flow through one channel is considered. The two-dimensional pressure distribution has been calculated by a time-dependent finite difference scheme. The boundary layer flow has been determined by different integral methods with special attention concerning the shock-boundary-layer interaction. Finally, the numerical results are compared with experiments, and the agreement is satisfactory.

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