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

**Physics Forums - The Fusion of Science and Community**

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

# Aerospace Oblique shock reflection on solid boundary

Loading...

Similar Threads - Oblique shock reflection | Date |
---|---|

Oblique Shock Angle | Mar 16, 2015 |

Stress on Oblique Plane | Oct 13, 2013 |

Aerospace Oblique and expansion waves? | May 4, 2011 |

Aerospace Oblique Shock Angle Calculation | Apr 12, 2010 |

Oblique + Normal Compression shock and nose cone angles | Aug 21, 2009 |

**Physics Forums - The Fusion of Science and Community**