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CL and CD

User: "Altair Forum User"
Altair Employee
Updated by Altair Forum User

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

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    User: "cfdguru"
    New Altair Community Member
    Updated by cfdguru

    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. 

    User: "Altair Forum User"
    Altair Employee
    OP
    Updated by Altair Forum User

    Hello sir,

    is it possible to do through user defined functions in acuprobe.

    User: "cfdguru"
    New Altair Community Member
    Updated by cfdguru

    Yes, you can use AcuProbe.