Imperial College London
Alternate

Emeritus ProfessorAnatolyRuban

Faculty of Natural Sciences, Department of Mathematics

Emeritus Professor
 
 
 
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Contact

 

+44 (0)20 7594 8498a.ruban

 
 
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Location

 

748Huxley BuildingSouth Kensington Campus

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Summary

 

Publications

Citation

BibTex format

@article{KOROLEV:2002:10.1017/s0022112002008777,
author = {KOROLEV, GL and GAJJAR, JSB and RUBAN, AI},
doi = {10.1017/s0022112002008777},
journal = {Journal of Fluid Mechanics},
pages = {173--199},
title = {Once again on the supersonic flow separation near a corner},
url = {http://dx.doi.org/10.1017/s0022112002008777},
volume = {463},
year = {2002}
}
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RIS format (EndNote, RefMan)

TY  - JOUR
AB  - <jats:p>Laminar boundary-layer separation in the supersonic flow past a corner point on a rigid body contour, also termed the compression ramp, is considered based on the viscous–inviscid interaction concept. The ‘triple-deck model’ is used to describe the interaction process. The governing equations of the interaction may be formally derived from the Navier–Stokes equations if the ramp angle θ is represented as θ = θ<jats:sub>0</jats:sub>Re<jats:sup>−1/4</jats:sup>, where θ<jats:sub>0</jats:sub> is an order-one quantity and <jats:italic>Re</jats:italic> is the Reynolds number, assumed large. To solve the interaction problem two numerical methods have been used. The first method employs a finite-difference approximation of the governing equations with respect to both the streamwise and wall-normal coordinates. The resulting algebraic equations are linearized using a Newton–Raphson strategy and then solved with the Thomas-matrix technique. The second method uses finite differences in the streamwise direction in combination with Chebychev collocation in the normal direction and Newton–Raphson linearization.</jats:p><jats:p>Our main concern is with the flow behaviour at large values of θ<jats:sub>0</jats:sub>. The calculations show that as the ramp angle θ<jats:sub>0</jats:sub> increases, additional eddies form near the corner point inside the separation region. The behaviour of the solution does not give any indication that there exists a critical value θ<jats:sup></jats:sup><jats:sub>0</jats:sub> of the ramp angle θ<jats:sub>0</jats:sub>, as suggested by Smith & Khorrami (1991) who claimed that as θ<jats:sub>0</jats:sub> approaches θ<jats:sup></jats:sup><jats:sub>0</jats:sub>, a singularity develop
AU  - KOROLEV,GL
AU  - GAJJAR,JSB
AU  - RUBAN,AI
DO  - 10.1017/s0022112002008777
EP  - 199
PY  - 2002///
SN  - 0022-1120
SP  - 173
TI  - Once again on the supersonic flow separation near a corner
T2  - Journal of Fluid Mechanics
UR  - http://dx.doi.org/10.1017/s0022112002008777
VL  - 463
ER  -
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