Effect of mach number on hypersonic flow past a delta wing with blunt edges

1970 ◽  
Vol 2 (1) ◽  
pp. 66-69
Author(s):  
A. V. Krasil'nikov
Keyword(s):  
Mach Number ◽  
Hypersonic Flow ◽  
Delta Wing ◽  
Flow Past

The Hypersonic Source Flow Past Wedges and Cones

1971 ◽  
Vol 22 (4) ◽  
pp. 327-345 ◽  
Author(s):  
M. A. Gorgui
Keyword(s):  
Mach Number ◽  
Hypersonic Flow ◽  
Perturbation Analysis ◽  
Flow Past ◽  
Source Flow

SummaryTo study the effects of flow non-uniformities on the hypersonic flow past test bodies, perturbation analysis is applied to the hypersonic source flow past wedges and cones. In both cases it is shown that the effects of the source flow on the shock shape and velocity are small, while effects on the pressure and density are large. Curves are presented for various values of the Mach number from which these effects can be estimated.

Hypersonic flow past delta wing of finite thickness

1973 ◽  
Vol 5 (3) ◽  
pp. 394-402 ◽  
Author(s):  
A. L. Gonor ◽  
N. A. Ostepenko
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Finite Thickness ◽  
Flow Past

Separated Flow Past a Slender Delta Wing at Incidence

1973 ◽  
Vol 24 (2) ◽  
pp. 120-128 ◽  
Author(s):  
J E Barsby
Keyword(s):  
Delta Wing ◽  
Separated Flow ◽  
Leading Edge ◽  
Vortex Sheet ◽  
Simultaneous Equations ◽  
Delta Wings ◽  
Nested Iteration ◽  
Finite Difference Technique ◽  
Flow Past ◽  
Vortex Systems

SummarySolutions to the problem of separated flow past slender delta wings for moderate values of a suitably defined incidence parameter have been calculated by Smith, using a vortex sheet model. By increasing the accuracy of the finite-difference technique, and by replacing Smith’s original nested iteration procedure, to solve the non-linear simultaneous equations that arise, by a Newton’s method, it is possible to extend the range of the incidence parameter over which solutions can be obtained. Furthermore for sufficiently small values of the incidence parameter, new and unexpected results in the form of vortex systems that originate inboard from the leading edge have been discovered. These new solutions are the only solutions, to the author’s knowledge, of a vortex sheet leaving a smooth surface.Interest has centred upon the shape of the finite vortex sheet, the position of the isolated vortex, and the lift, and variations of these quantities are shown as functions of the incidence parameter. Although no experimental evidence is available, comparisons are made with the simpler Brown and Michael model in which all the vorticity is assumed to be concentrated onto an isolated line vortex. Agreement between these two models becomes very close as the value of the incidence parameter is reduced.

The supersonic and low-speed flows past circular cylinders of finite length supported at one end

1962 ◽  
Vol 12 (3) ◽  
pp. 367-387 ◽  
Author(s):  
D. M. Sykes
Keyword(s):  
Mach Number ◽  
Finite Length ◽  
Central Region ◽  
Diameter Ratio ◽  
Circular Cylinders ◽  
Form Drag ◽  
Drag Coefficients ◽  
Low Speed ◽  
Flow Past ◽  
Length To Diameter Ratio

The flow past circular cylinders of finite length, supported at one end and lying with their axes perpendicular to a uniform stream, has been investigated in a supersonic stream at Mach number 1.96 and also in a low-speed stream. In both stream it was found that the flow past the cylinders could be divided into three regions: (a) a central region, (b) that near the free end of the cylinder, and (c) that near the supported end. The locations of the second and third regions were found to be almost independent of the cylinder length-to-diameter ratio, provided that this exceeded 4, while the flow within and the extent of the first region were dependent on this ratio. Form-drag coefficients determined in the central region in the supersonic flow were in close agreement with the values determined at the same Mach number by other workers. In the low-speed flow the local form-drag coefficients were dependent on length-to-diameter ratio and were always less than that of an infinite-length cylinder at the same Reynolds number.

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