Numerical simulation of laminar viscous supersonic flow past a two-dimensional cavity

1994 ◽  
Vol 29 (6) ◽  
pp. 759-764 ◽  
Author(s):  
A. D. Savelyev
Keyword(s):  
Numerical Simulation ◽  
Supersonic Flow ◽  
Two Dimensional ◽  
Flow Past

Supersonic Flow Past a Wedge with a Flame at its Apex

1968 ◽  
Vol 19 (1) ◽  
pp. 80-90 ◽  
Author(s):  
R. Foster ◽  
J. F. Clarke
Keyword(s):  
Supersonic Flow ◽  
Flame Front ◽  
Flow Patterns ◽  
Chemical Energy ◽  
Two Dimensional ◽  
Pressure Flow ◽  
Simple Waves ◽  
Flow Past ◽  
Flow Deflection ◽  
Plane Flame

SummaryThe wholly supersonic flow past a two-dimensional wedge is analysed on the assumption that release of chemical energy into the stream can be accomplished across a thin discontinuous plane flame front attached to the apex. Forces experienced by the wedge are calculated and representative flow patterns exhibited. Some typical interactions between the flame and shocks or centred simple waves are discussed, with emphasis on the use of pressure-flow-deflection diagrams to obtain results.

Numerical Simulation of Energy Deposition in a Supersonic Flow Past a Hemisphere

2014 ◽  
Author(s):  
Mahsa Mortazavi ◽  
Doyle D. Knight ◽  
Olga A. Azarova ◽  
Jingchang Shi ◽  
Hong Yan
Keyword(s):  
Numerical Simulation ◽  
Supersonic Flow ◽  
Energy Deposition ◽  
Flow Past

Numerical Investigation of Viscous Laminar Supersonic Flow Past an Asymmetric Biconvex Circular-Arc Aerofoil

2013 ◽  
Vol 390 ◽  
pp. 147-151
Author(s):  
Saif Akram ◽  
Nadeem Hasan ◽  
Aqib Khan
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Supersonic Flow ◽  
Numerical Investigation ◽  
Lower Surface ◽  
Two Dimensional ◽  
Circular Arc ◽  
Flow Past ◽  
Supersonic Regime ◽  
Force Characteristics

A numerical investigation of two-dimensional unsteady, viscous and laminar compressible flow past an asymmetric biconvex circular-arc aerofoil in supersonic regime is carried out. The focus of the present work is to investigate the effects of variation of Mach number, at two different angles of attack, on the flow and force characteristics on NACA 2S-(50)(04)-(50)(20) aerofoil. The value of Reynolds number is taken as 5x105. The computations are carried out at Mach numbers of 1.25, 1.5 and 2.0 at an angle of attack of α=0° and α=10°. It is found that the aerofoil works well in the supersonic flow and, unlike the conventional symmetric biconvex aerofoil, generates finite lift at α=0° due to stronger shock waves at the lower surface. Moreover, the L/D ratio at α=10° is always found to be more than 2.5.

A Theory of Uniform Supersonic Flow Past a Thin Oscillating Aerofoil at Appreciable Incidence to the Main Stream

1954 ◽  
Vol 5 (4) ◽  
pp. 185-194
Author(s):  
Geoffrey L. Sewell
Keyword(s):  
Supersonic Flow ◽  
Main Stream ◽  
Angle Of Incidence ◽  
Two Dimensional ◽  
Fixed Position ◽  
Small Oscillations ◽  
Flow Past ◽  
Special Case ◽  
Number Of Authors

SummaryA number of authors (e.g., Refs. 1 and 2) have dealt with the problem of uniform two-dimensional supersonic flow past a thin oscillating aerofoil, whose angle of incidence to the main stream is small. In this special case, the effects of vorticity are negligible, while the fields of flow on either side of the aerofoil may be treated on the same footing.The object of this paper is to deal with the more general case in which the aerofoil performs small oscillations about a fixed position, in which its incidence to the main stream is appreciable.

scholarly journals Numerical simulation of two-dimensional laminar unsteady flow past a right trapezoidal cylinder at low Reynolds number: study of sharpening angle, time step, grid independence and domain size

2018 ◽  
Vol 192 ◽  
pp. 02030
Author(s):  
Sodsai Lamtharn ◽  
Monsak Pimsarn
Keyword(s):  
Numerical Simulation ◽  
Reynolds Number ◽  
Unsteady Flow ◽  
Strouhal Number ◽  
Domain Size ◽  
Two Dimensional ◽  
Time Step ◽  
Flow Past ◽  
The Right ◽  
Grid Independence

Numerical simulation of two-dimensional laminar unsteady flow past a right trapezoidal cylinder at low Reynolds number (Re = 100), zero of the flow approaching angle and sharpening angle of the right trapezoidal of 22.5° with a side ratio B/A = 1 are carried out to provide moreapplicable data for engineering design of barred tee in aspect of structural integrity. A finite volume method, non-uniform meshing with second-order implicit time discretization into eight-node quadratic quadrilateral finite elements is employed. An incompressible flow SIMPLEC code with constant fluid properties is used. The convective terms using a third-order QUICK scheme. The numerical simulation result is compared against the published results of flow past a square cylinder. The effect of sharpening angle on the response of the right trapezoidal cylinder is investigated. A special study of the effects of flow on significant factor for time step, grid independence, blockage ratio, domain size, upstream and downstream extents, size domain next to cylinder and size domain extent are performed systematically. The Strouhal number and RMS lift coefficients of fully saturated flow are calculated. The result shown that increasing of sharpening angle, the Strouhal number is negligible changed whilst the RMS lift coefficients significantly increased.

Numerical simulation of supersonic flow past a plate with surface material sublimation

2020 ◽  
Vol 27 (1) ◽  
pp. 81-88
Author(s):  
S. A. Gaponov ◽  
A. N. Semenov ◽  
B. V. Smorodsky
Keyword(s):  
Numerical Simulation ◽  
Supersonic Flow ◽  
Surface Material ◽  
Flow Past
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