Simple method of supersonic flow visualization using watertable

AIAA Journal ◽  
1995 ◽  
Vol 33 (1) ◽  
pp. 181-182 ◽  
Author(s):  
A. K. Pal ◽  
B. Bose
Keyword(s):  
Supersonic Flow ◽  
Flow Visualization ◽  
Simple Method ◽  
Supersonic Flow Visualization

Simple method of supersonic flow visualization using smoke

AIAA Journal ◽  
1992 ◽  
Vol 30 (1) ◽  
pp. 278-279 ◽  
Author(s):  
L. S. Miller ◽  
E. Irani
Keyword(s):  
Supersonic Flow ◽  
Flow Visualization ◽  
Simple Method ◽  
Supersonic Flow Visualization

scholarly journals Numerical flow visualization of supersonic flow using OpenFOAM®

2020 ◽  
Author(s):  
Aravind Satheesh Kumar ◽  
Pujan Dubey ◽  
B. T. Kannan
Keyword(s):  
Supersonic Flow ◽  
Flow Visualization

Flow Visualization of Supersonic Flow over a Finite Cylinder

2012 ◽  
Vol 29 (8) ◽  
pp. 084702 ◽  
Author(s):  
Deng-Pan Wang ◽  
Yu-Xin Zhao ◽  
Zhi-Xun Xia ◽  
Qing-Hua Wang ◽  
Zhen-Bing Luo
Keyword(s):  
Supersonic Flow ◽  
Flow Visualization ◽  
Finite Cylinder

The internal flow problem in axi-symmetric supersonic flow

1958 ◽  
Vol 251 (987) ◽  
pp. 1-21 ◽  
Keyword(s):  
Supersonic Flow ◽  
Flow Problem ◽  
Natural Extension ◽  
Internal Flow ◽  
Wave Fronts ◽  
Simple Method ◽  
Circular Duct ◽  
Linearized Equations ◽  
Velocity Gradients ◽  
Ordinary Solution

A scheme of approximate solution is presented for the supersonic flow in a circular duct of slowly varying cross-section for the cases when the conventional linearized theory fails. This happens whenever there are regions in the flow field, termed wave fronts, where the velocity gradients are large in comparison with the variations in velocity. A careful discussion suggests that a valid first approximation may be obtained from a solution of the linearized equations by placing the solution on Mach linees computed from the solution. This is a natural extension of Whitham’s method for the external flow problem. However, it does not suffice to use the ordinary solution of the linearized equations as this possesses singularities. It is necessary to obtain a solution of the linearized equations satisfying boundary conditions in which due allowance has been made for the non-parallelism of the Mach lines. Within the accuracy of the approximation, this solution is found to agree with the ordinary solution away from the wave fronts but differs markedly within them. A simple method is obtained for converting the singular portions of the ordinary solution into a form valid within wave fronts. The problem, studied by Meyer and Ward, of an expansive discontinuity in the slope of the wall of the duct is discussed and the details of the flow are clarified. It is shown that both the velocity and the velocity gradients are finite on the Mach lines where previous theories predicted singularities. Nevertheless, a shock wave is formed in the reflexion of the expansion wave from the axis of the duct, no matter how small the initial disturbance.

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