Guys,

As you may know, you can calculate the shock angle of a cone using taylor-maccoll equation for any incoming flow with different Mach number but why there is no way to calculate the shock angle in a convergent conical duct(funnel duct)? something just like this:

https://media.springernature.com/original/springer-static/image/art%3A10.1007%2Fs00193-016-0700-x/MediaObjects/193_2016_700_Fig1_HTML.gif

Reference of the image:

Article Patterns of steady axisymmetric supersonic compression flows...

Any idea to calculate the shock angle in a convergent conical duct(funnel duct)?

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