Calculation of unsteady supersonic flow past a two-dimensional cascade of plates ween vorticity inhomogeneities of the flow act on it

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.

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Unsteady supersonic flow past a harmonically pitching and plunging cone

10.2514/6.1981-1874 ◽

1981 ◽

Keyword(s):

Supersonic Flow ◽

Flow Past ◽

Unsteady Supersonic Flow

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

Fluid Dynamics ◽

10.1007/bf02040782 ◽

1994 ◽

Vol 29 (6) ◽

pp. 759-764 ◽

Cited By ~ 1

Author(s):

A. D. Savelyev

Keyword(s):

Numerical Simulation ◽

Supersonic Flow ◽

Two Dimensional ◽

Flow Past

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

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.390.147 ◽

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.

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

Aeronautical Quarterly ◽

10.1017/s0001925900001189 ◽

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.

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