Numerical Solution of Subcritical Flow Past Airfoils

1973 ◽  
Author(s):  
Ernest O. Rogers
2012 ◽  
Vol 24 (2) ◽  
pp. 213-230 ◽  
Author(s):  
R. J. HOLMES ◽  
G. C. HOCKING ◽  
L. K. FORBES ◽  
N. Y. BAILLARD

The subcritical flow of a stream over a bottom obstruction or depression is considered with particular interest in obtaining solutions with no downstream waves. In the linearised problem this can always be achieved by superposition of multiple obstructions, but it is not clear whether this is possible in a full nonlinear problem. Solutions computed here indicate that there is an effective nonlinear superposition principle at work as no special shape modifications were required to obtain wave-cancelling solutions. Waveless solutions corresponding to one or more trapped waves are computed at a range of different Froude numbers and are shown to provide a rather elaborate mosaic of solution curves in parameter space when both negative and positive obstruction heights are included.


AIAA Journal ◽  
1987 ◽  
Vol 25 (9) ◽  
pp. 1171-1175 ◽  
Author(s):  
S-M. Liang ◽  
K-Y. Fung

2013 ◽  
Vol 18 (3) ◽  
pp. 761-777
Author(s):  
M. Patel ◽  
M.G. Timol

Abstract A similarity analysis of non-Newtonian fluid flow past an accelerated vertical infinite plate in the presence of free convection current is carried out. A group theoretic generalized dimensional analysis is employed to achieve the governing non-linear ordinary differential equations in the most general form. Numerical solutions of these equations are given with the plot of their velocity profiles with the effects of Pr-Prandtl number and Gr-Grashof number


1986 ◽  
Vol 170 ◽  
pp. 253-264 ◽  
Author(s):  
M. G. Hill ◽  
N. Riley

A method for calculating transonic potential flow past a multi-element aerofoil configuration is presented. The method is a hybrid method that is based upon a compressible-flow panel method, valid for subcritical flow, and a finite-difference method that is suitable for supercritical flow calculations. The effectiveness of the proposed method is demonstrated, first by application to a single aerofoil and then to a three-element aerofoil.


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