Transonic flow past an aerofoil with shock waves

1964 ◽  
pp. 126-136
Author(s):  
A. B. Tayler
Keyword(s):  
Shock Waves ◽  
Transonic Flow ◽  
Flow Past

scholarly journals ANALYSIS OF TRANSONIC FLOW PAST CUSPED AIRFOILS

2015 ◽  
Vol 55 (3) ◽  
pp. 193-198
Author(s):  
Jiří Stodůlka ◽  
Pavel Šafařík
Keyword(s):  
Shock Waves ◽  
Transonic Flow ◽  
Flow Behavior ◽  
Flow Past ◽  
Trailing Edges ◽  
Oblique Shocks

Transonic flow past two cusped airfoils is numerically solved and achieved results are analyzed by means of flow behavior and oblique shocks formation.Regions around sharp trailing edges are studied in detail and parameters of shock waves are solved and compared using classical shock polar approach and verified by reduction parameters for symmetric configurations.

Prediction of Viscous Effects in Steady Transonic Flow Past an Aerofoil

1979 ◽  
Vol 30 (3) ◽  
pp. 485-505 ◽  
Author(s):  
M.R. Collyer ◽  
R.C. Lock
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Transonic Flow ◽  
Lift Coefficient ◽  
Inviscid Flow ◽  
Viscous Effects ◽  
Flow Past ◽  
Boundary Layer Development ◽  
Transition Position ◽  
Realistic Representation

SummaryAn account is given of a numerical method for calculating transonic flow past an aerofoil with an allowance for viscous effects, providing that the boundary layer remains fully attached over the aerofoil surface. The method has been developed by combining, in an iterative manner, calculations of the inviscid flow with calculations of the compressible boundary layer and wake. The solution for the inviscid flow is obtained by an iterative scheme, originally established by Garabedian & Korn, which has been modified to give a more realistic representation of shock waves. The boundary-layer development is treated as laminar initially; at a certain transition position a turbulent boundary layer is assumed to develop, and this is determined by the lag-entrainment method of Green et al. Comparisons of the results from the numerical scheme with some experimental measurements are shown for various examples in which shock waves of moderate strength are present. The method predicts, with reasonable accuracy, both the detailed pressure distribution and the variation of drag coefficient with lift coefficient.

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

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.

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.

Perturbation Procedures for Nonlinear Viscous Flows

1983 ◽  
Vol 50 (2) ◽  
pp. 265-269
Author(s):  
D. Nixon
Keyword(s):  
Perturbation Theory ◽  
Shock Waves ◽  
Transonic Flow ◽  
Stokes Equations ◽  
Viscous Flows ◽  
Two Dimensions ◽  
Experimental Results ◽  
Navier Stokes ◽  
Navier Stokes Equations

The perturbation theory for transonic flow is further developed for solutions of the Navier-Stokes equations in two dimensions or for experimental results. The strained coordinate technique is used to treat changes in location of any shock waves or large gradients.

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