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

**Physics Forums | Science Articles, Homework Help, Discussion**

Join Physics Forums Today!

The friendliest, high quality science and math community on the planet! Everyone who loves science is here!

The friendliest, high quality science and math community on the planet! Everyone who loves science is here!

# Oblique Shock Angle

**Physics Forums | Science Articles, Homework Help, Discussion**