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Design of a Planar Supersonic Wind Tunnel Nozzle |
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August 16, 2024, 05:06 |
Design of a Planar Supersonic Wind Tunnel Nozzle
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#1 |
New Member
Join Date: Apr 2024
Location: India
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Hello everyone,
I am trying to make a MATLAB code to design a 2D planar nozzle with uniform outflow for use in a wind tunnel. I am using the method of characteristics approach and following the book "Gas Dynamics Vol II by Maurice J. Zucrow and Joe D. Hoffman". I have made the initial value line and its extension. However, I am facing a lot of difficulties in generating the initial expansion curve or finding particular theta and the corresponding kernel region for a desired design Mach Number. Also, Zucrow talks about mass flow rate conservation to generate the straightening section which I am quite confused on how to incorporate into the code. I am still looking into Cory Dodson's code on GitHub https://github.com/corydodson/NozzleDesign. Although when I run the code, singularities show up and I am still trying to debug it. Are there any books, resources, codes (MATLAB) which uses Zucrow's method and talks about the design in detail ? Any help is appreciated! Thank you! |
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August 16, 2024, 05:26 |
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#2 | |
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Filippo Maria Denaro
Join Date: Jul 2010
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Quote:
Not sure if I remember well, in the Zucrow textbook there is the Fortran code, isn't it? |
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August 16, 2024, 06:01 |
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#3 | |
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I believe I need to iterate over a set of theta angles, generating the corresponding kernel region for each theta and check whether the desired mach number at the axis has been reached or not for that value of Theta. |
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August 16, 2024, 17:57 |
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#4 |
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Lucky
Join Date: Apr 2011
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Yes of course you need to iterate something to get what you desire, that's what "design" means. Otherwise, there wouldn't be any need to design something, you would just click the "Add to cart" button
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August 17, 2024, 17:33 |
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#5 | |
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Filippo Maria Denaro
Join Date: Jul 2010
Posts: 6,855
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Despite the fact that for expansion flows you can use Riemann invariants to get the exact solution, there is always an equation that need to be solved by iteration method to get the solution. This is what happens for unsteady flows as well as for steady flows for both direct and inverse problems. |
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Tags |
contour, gas dynamics, moc, nozzle analysis, zucrow |
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