scholarly journals Study on Waves Generated by a Planing Flat Plate-VIII : Numerical Computation on Waves Generated by a Planing Flat Plate of Finite Span

1996 ◽  
Vol 95 (0) ◽  
pp. 223-231
Author(s):  
Shigeaki SHIOTANI
Keyword(s):  
Flat Plate ◽  
Numerical Computation ◽  
Plate Viii ◽  
Finite Span

Linear stability of a cylindrical falling film

1987 ◽  
Vol 183 ◽  
pp. 365-377 ◽  
Author(s):  
Francisco J. Solorio ◽  
Mihir Sen
Keyword(s):  
Reynolds Number ◽  
Flat Plate ◽  
Numerical Computation ◽  
Linear Stability ◽  
Weber Number ◽  
Perturbation Technique ◽  
Reynolds Numbers ◽  
Falling Film ◽  
Fully Developed Flow ◽  
Long Cylinder

The problem of a cylindrical falling film, descending vertically outside an infinitely long cylinder is considered. The linear stability of the fully developed flow is studied, first with a perturbation technique for small wavenumbers, and then by direct numerical computation. The numerical results are in agreement with other published values for the cylindrical jet and flat plate limits. The study shows that the cylindrical falling film is unstable for all Reynolds numbers, Weber numbers and radius ratios. Stability and amplification curves are calculated for different values of the parameters. With increasing curvature of the film the range of unstable wavenumbers and the wavenumber of the most amplified wave increase. For low curvature the wavenumber of the most amplified wave decreases with Reynolds number or Weber number, while for high curvatures it increases.

Numerical Computation of Nonstationary Aerodynamics of Flat Plate Cascades in Compressible Flow

1976 ◽  
Vol 98 (2) ◽  
pp. 165-170 ◽  
Author(s):  
R. H. Ni ◽  
F. Sisto
Keyword(s):  
Flat Plate ◽  
Numerical Computation ◽  
Compressible Flow ◽  
Computational Domain ◽  
Two Dimensional ◽  
Order Of Accuracy ◽  
Fluid Properties ◽  
Time Marching ◽  
Interblade Phase Angle ◽  
Good Agreement

The “time marching” technique is successfully applied to the numerical computation of the nonstationary aerodynamics of a flat plate cascade for compressible flow of either subsonic or supersonic nature. The unsteady perturbation amplitudes of fluid properties are used as the dependent variables so that the computational domain can be reduced to a two-dimensional channel guided by two adjacent blades for any interblade phase angle. A new method of handling the boundary condition is developed in which the order of accuracy for the boundary points will be the same as the interior points. The wake region behind the trailing edge of each blade is treated as a “slip plane” as done in two-dimensional steady state supersonic flow. Results are in good agreement with existing analytical solutions.

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