Laser Velocimetry Applied to Transonic Flow Past Airfoils

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

10.2514/6.2000-125 ◽

2000 ◽

Cited By ~ 1

Author(s):

Yoshiatsu Oki ◽

Takeshi Sakata ◽

Naoki Uchiyama ◽

Takeshi Kaiden ◽

Takeshi Andoh

Keyword(s):

Numerical Simulation ◽

Transonic Flow ◽

Flow Past

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Transonic flow past finite wedges

Mathematical Proceedings of the Cambridge Philosophical Society ◽

10.1017/s030500410002747x ◽

1952 ◽

Vol 48 (1) ◽

pp. 178-187 ◽

Cited By ~ 5

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.

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Transonic flow past an aerofoil with shock waves

Symposium Transsonicum ◽

10.1007/978-3-642-88337-8_10 ◽

1964 ◽

pp. 126-136

Author(s):

A. B. Tayler

Keyword(s):

Shock Waves ◽

Transonic Flow ◽

Flow Past

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Mathematical Problems in Transonic Flow

Canadian Mathematical Bulletin ◽

10.4153/cmb-1986-023-3 ◽

1986 ◽

Vol 29 (2) ◽

pp. 129-139 ◽

Cited By ~ 3

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.

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Instability of transonic flow past flattened airfoils

Open Engineering ◽

10.2478/s13531-013-0124-7 ◽

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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