I am currently studying the flow on 3d airfoil with and without winglets and the aero plane is at 7500m altitude. the Mach number is 0.4. I am using the incompressible flow with air density changed to ideal gas law. now my question is at 7500m the pressure is lesser than 101325Pa its around 40000Pa something and the temperature is also lesser than usual environment temperature? so my question is how to tell fluent that the environment or the flow is at 7500m altitude. Should i change the operating pressure from 101325 to 40000pa which is at 7500m and should is give temperature inlet at 7500m at inlet or it is wrong and then what's the solution?
You can set the operating pressure to zero and specify the inlet pressure equal to the pressure at 7500m.
But at inlet I need to use pressure far field or velocity inlet. How can I give pressure inlet boundary condition then?
Since you have both Mach number and pressure, you can use pressure far-field condition. You can also define the temperature in pressure far-field boundary conditions.
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