Is there an equation to calculate the oblique shock angle for supersonic flow when the given angle of attack is greater than 0, but less than the half angle?(adsbygoogle = window.adsbygoogle || []).push({});

In my particular practical experiment, the half angle of the aerofoil is 5 degrees, so want to get a variety of figures between 5 and -5 as I know expansion waves begin when the angle is increased to greater than the half angle.

Thanks in advance

Harry

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# Oblique Shock Angle

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