How to set AOA for an Airfoil in CFX?
I am using CFX 13, and I want to do analysis of a half delta wing which is at an AOA of 5 deg. At inlet I am giving Total pressure values, and in the flow direction I am giving the unit vector components along X and Z directions. My question is are the settings correct and Does the direction components in flow direction tab take unit vector values or Actual velocity components. Or is der any other method for doing so.
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