Hi guys, i need some help on this topic.(adsbygoogle = window.adsbygoogle || []).push({});

Basically, i need to calculate the angle of reflection of a oblique shock on a solid boundary.

Here is the description of the question i have:

an incident supersonic flow reaches a compression corner, with a deflection angle of 15 degrees. Mach number of the inlet flow is 2.6, and static temperature is 288k.

above the compression corner, there is an upper horizontal wall, where the oblique shock would hit and then be reflected. Calculate the angle of reflection of the shock by the upper wall.

What i know:

1. i could calculate the mach number after the flow passes the first shock, as well as the new direction of the flow (15 degrees to floor)

2. I know that the final direction of the supersonic flow would have to be parallel to the upper wall, which means it must be at 0 degrees.

apart from this, i have no idea how the shock would be reflected.

Is there any relationship between the deflected angle and the angle of the oblique shock? or between the change in normal velocity component of the flow to the deflected angle/shock angle?

thank you very much guys!

regards

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# Aerospace Oblique shock reflection on solid boundary

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