I am modelling a flow over a turbine bade in a passage. The turbine blade is stationary and not rotating.
I give the total pressure and Temperature at the inlet and Static pressure at the outlet.
The mach number calculated does not match with experimental data.
Can anyone guide me is it going to effect my results.
Actually i want that the flow conditions in my CFD simulation should be same as one measured in Wind tunnel tests.
I think for similar flows the Re and mach number should be same. IF it is so, how can i match my Re and Mach number with data in the wind tunnel
Any help will be appreciated
have you used the same reference chord, pressure, temperature, density realized in the wind tunnel? If so, then your simulation can be somehow approximated but it must provide the same order of magnitude. Otherwise some setting in the code is wrong
All geometric dimensions are same as in experiments. Pressures and temperatures were measured during tests and air as an ideal gas is used for the calculation.
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