Numerical Solution of the Supersonic and Hypersonic Viscous Flow around Thin Delta Wings

AIAA Journal ◽  
1979 ◽  
Vol 17 (9) ◽  
pp. 942-949 ◽  
Author(s):  
Guion S. Bluford
AIAA Journal ◽  
1982 ◽  
Vol 20 (2) ◽  
pp. 203-210 ◽  
Author(s):  
J. C. Tannehill ◽  
Ethiraj Venkatapathy ◽  
John V. Rakich

1958 ◽  
Vol 4 (1) ◽  
pp. 81-86 ◽  
Author(s):  
R. B. Payne

A numerical solution has been obtained for the starting flow of a viscous fluid past a circular cylinder at Reynolds numbers 40 and 100. The method used is the step-by-step forward integration in time of Helmholtz's vorticity equation. The advantage of working with the vorticity is that calculations can be confined to the region of non-zero vorticity near the cylinder.The general features of the flow, including the formation of the eddies attached to the rear of the cylinder, have been determined, and the drag has been calculated. At R = 40 the drag on the cylinder decreases with time to a value very near that for the steady flow.


2016 ◽  
Vol 2016 ◽  
pp. 1-6 ◽  
Author(s):  
Hossein Aminikhah ◽  
Somayyeh Kazemi

A numerical method is proposed to study the laminar boundary layer about a flat plate in a uniform stream of fluid. The presented method is based on the quartic B-spline approximations with minimizing the error L2-norm. Theoretical considerations are discussed. The computed results are compared with some numerical results to show the efficiency of the proposed approach.


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