Influence of intensive suction on the flow in the neighborhood of a laminar-boundary-layer separation point in a supersonic flow

1975 ◽  
Vol 9 (2) ◽  
pp. 173-178
Author(s):  
I. I. Lipatov ◽  
V. Ya. Neiland
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Laminar Boundary Layer ◽  
Boundary Layer Separation ◽  
Separation Point ◽  
Layer Separation

On quasi-steady boundary-layer separation in supersonic flow. Part 2. Downstream moving separation point

2020 ◽  
Vol 900 ◽  
Author(s):  
A. I. Ruban ◽  
A. Djehizian ◽  
J. Kirsten ◽  
M. A. Kravtsova
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Boundary Layer Separation ◽  
Separation Point ◽  
Layer Separation ◽  
Flow Part ◽  
Image Position

Abstract

scholarly journals On unsteady boundary-layer separation in supersonic flow. Part 1. Upstream moving separation point

2011 ◽  
Vol 678 ◽  
pp. 124-155 ◽  
Author(s):  
A. I. RUBAN ◽  
D. ARAKI ◽  
R. YAPALPARVI ◽  
J. S. B. GAJJAR
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Supersonic Flow ◽  
Body Surface ◽  
Boundary Layer Separation ◽  
The Body ◽  
Separation Point ◽  
Coordinate Frame ◽  
Characteristic Time Scale ◽  
Layer Separation

This study is concerned with the boundary-layer separation from a rigid body surface in unsteady two-dimensional laminar supersonic flow. The separation is assumed to be provoked by a shock wave impinging upon the boundary layer at a point that moves with speed Vsh along the body surface. The strength of the shock and its speed Vsh are allowed to vary with time t, but not too fast, namely, we assume that the characteristic time scale t ≪ Re−1/2/Vw2. Here Re denotes the Reynolds number, and Vw = −Vsh is wall velocity referred to the gas velocity V∞ in the free stream. We show that under this assumption the flow in the region of interaction between the shock and boundary layer may be treated as quasi-steady if it is considered in the coordinate frame moving with the shock. We start with the flow regime when Vw = O(Re−1/8). In this case, the interaction between the shock and boundary layer is described by classical triple-deck theory. The main modification to the usual triple-deck formulation is that in the moving frame the body surface is no longer stationary; it moves with the speed Vw = −Vsh. The corresponding solutions of the triple-deck equations have been constructed numerically. For this purpose, we use a numerical technique based on finite differencing along the streamwise direction and Chebyshev collocation in the direction normal to the body surface. In the second part of the paper, we assume that 1 ≫ Vw ≫ O(Re−1/8), and concentrate our attention on the self-induced separation of the boundary layer. Assuming, as before, that the Reynolds number, Re, is large, the method of matched asymptotic expansions is used to construct the corresponding solutions of the Navier–Stokes equations in a vicinity of the separation point.

Theory of laminar boundary layer separation in supersonic flow

1972 ◽  
Vol 4 (4) ◽  
pp. 33-35 ◽  
Author(s):  
V. Ya. Neiland
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Laminar Boundary Layer ◽  
Boundary Layer Separation ◽  
Layer Separation

Laminar boundary layer separation over a fluttering panel induced by an oblique shock wave

2019 ◽  
Vol 90 ◽  
pp. 90-109 ◽  
Author(s):  
Yingkun Li ◽  
Haoxiang Luo ◽  
Xiong Chen ◽  
Jinsheng Xu
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Laminar Boundary Layer ◽  
Boundary Layer Separation ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Layer Separation

An investigation of the effect of suction on hypersonic laminar boundary-layer separation.

AIAA Journal ◽  
1968 ◽  
Vol 6 (2) ◽  
pp. 239-243 ◽  
Author(s):  
K. O. W. BALL ◽  
R. H. KORKEGI
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
Boundary Layer Separation ◽  
Layer Separation
Sign in / Sign up

Export Citation Format

Share Document