Transonic flow past finite wedges

1952 ◽  
Vol 48 (1) ◽  
pp. 178-187 ◽  
Author(s):  
A. G. Mackie ◽  
D. C. Pack
Keyword(s):  
Incompressible Fluid ◽  
Critical Velocity ◽  
Speed Of Sound ◽  
Compressible Fluid ◽  
Transonic Flow ◽  
Ideal Gas ◽  
Hodograph Method ◽  
Subsonic Velocity ◽  
Flow Past ◽  
Axis Of Symmetry

AbstractThe solution for the flow of an incompressible fluid past an infinitely long wedge with a finite sloping edge (a finite wedge) is generalized by the hodograph method. In the flow thus obtained the axis of symmetry and a sloping edge of the wedge are again part of one streamline. It becomes possible to describe the flow of an ideal gas past a finite wedge if the hypothesis is made that the first singularity on this streamline, along the sloping edge, corresponds to the shoulder of the wedge. For a given wedge, with gradually increasing velocity at infinity upstream, the singularity appears at first at subsonic velocity. Beyond a certain critical velocity at infinity the singularity is always associated with the speed of sound. The hypothesis thus implies that put forward by Maccoll(9) and supported by Busemann(l). A qualitative examination shows that the solution reproduces experimentally known features of the flow of compressible fluid past a finite wedge.

An application of the Weber-Orr transform to the problem of transonic flow past a finite wedge in a channel

1958 ◽  
Vol 54 (3) ◽  
pp. 391-395 ◽  
Author(s):  
J. B. Helliwell
Keyword(s):  
Flow Pattern ◽  
Transonic Flow ◽  
Free Stream ◽  
Wedge Angle ◽  
Stream Line ◽  
Subsequent Paper ◽  
Inviscid Fluid ◽  
Subsonic Velocity ◽  
Flow Past ◽  
Two Dimensional Flow

In an earlier paper (Helliwell and Mackie(3)) it was shown that steady two-dimensional flow patterns of a compressible inviscid fluid at high subsonic speed past a finite wedge could be determined quite simply when sonic velocity is attained at the shoulder of the wedge and thereafter the flow breaks away from the shoulder with a free streamline. In a subsequent paper (Helliwell (4)) a similar method of analysis has been applied to determine a flow pattern of the same general type past a finite wedge symmetrically placed in a channel, from which the case of the wedge in the free stream may be deduced as a special case. However, in a general investigation into transonic flow past wedges (Mackie and Pack (5)) it was argued that when the wedge angle or the free stream (subsonic) velocity is too small no supersonic region would develop on the wedge side, and the flow would break away from the wedge shoulder with some higher subsonic velocity, giving a free stream line. The present note examines the flow pattern which develops under these conditions for a wedge symmetrically placed in a channel with parallel walls.

Numerical simulation of transonic flow past an F-16A aircraft configuration using CASPER

2000 ◽  
Author(s):  
Yoshiatsu Oki ◽  
Takeshi Sakata ◽  
Naoki Uchiyama ◽  
Takeshi Kaiden ◽  
Takeshi Andoh
Keyword(s):  
Numerical Simulation ◽  
Transonic Flow ◽  
Flow Past

scholarly journals Integration of the boundary-layer equations for a plane in a compressible fluid

1948 ◽  
Vol 195 (1041) ◽  
pp. 180-188 ◽  
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Prandtl Number ◽  
Incompressible Fluid ◽  
Satisfactory Agreement ◽  
Asymptotic Method ◽  
Compressible Fluid ◽  
Boundary Layer Equations ◽  
Rapid Calculation ◽  
Elementary Methods

The aim of this paper is to integrate Emmons & Brainerd’s equations analytically for arbitrary values of the Prandtl number and the Mach number, using the powerful asymptotic method of integration developed by the author in a previous paper (Meksyn 1948), dealing with the boundary layer in an incompressible fluid. It is shown here that in the first approximations the asymptotic integration gives ample accuracy and that it can be determined by simple and elementary methods. The results of this comparatively rapid calculation are in very satisfactory agreement with the results of the lengthy numerical calculations made by Emmons & Brainerd for certain specific values of Prandtl number and Mach number.

Mathematical Problems in Transonic Flow

1986 ◽  
Vol 29 (2) ◽  
pp. 129-139 ◽  
Author(s):  
Cathleen Synge Morawetz
Keyword(s):  
Compressible Flow ◽  
Transonic Flow ◽  
Supersonic Flight ◽  
Flow Past ◽  
Mathematical Problems

AbstractWe present an outline of the problem of irrotational compressible flow past an airfoil at speeds that lie somewhere between those of the supersonic flight of the Concorde and the subsonic flight of commercial airlines. The problem is simplified and the important role of modifying the equations with physics terms is examined.

scholarly journals Instability of transonic flow past flattened airfoils

2013 ◽  
Vol 3 (4) ◽  
Author(s):  
Alexander Kuzmin
Keyword(s):  
Numerical Modeling ◽  
Transonic Flow ◽  
Stokes Equations ◽  
Lift Coefficient ◽  
Reynolds Numbers ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Flow Simulations ◽  
Flow Past ◽  
Coefficient Versus

AbstractTransonic flow past a Whitcomb airfoil and two modifications of it at Reynolds numbers of the order of ten millions is studied. The numerical modeling is based on the system of Reynolds-averaged Navier-Stokes equations. The flow simulations show that variations of the lift coefficient versus the angle of attack become more abrupt with decreasing curvature of the airfoil in the midchord region. This is caused by an instability of closely spaced local supersonic regions on the upper surface of the airfoil.

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