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I am Working on a Flow over a airfoil case.so how to plot Cl and CD values In acusolve.Kindly help me with steps or any case file related to aerodynamics to approach the Airfoil study
Cl and Cd can be computed based on the surface output values for traction. The traction represents the force on the airfoil. Knowing the force and angle of attack, you can easily compute the lift and drag coefficients. This can be done using acuProbe, or you can convert the data to table format and use your favorite spreadsheet or plotting program.
Hello sir,
is it possible to do through user defined functions in acuprobe.
Yes, you can use AcuProbe.
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