CL and CD

Altair Forum User
Altair Forum User
Altair Employee
edited October 2020 in Community Q&A

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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Answers

  • cfdguru
    cfdguru New Altair Community Member
    edited July 2014

    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. 

  • Altair Forum User
    Altair Forum User
    Altair Employee
    edited July 2014

    Hello sir,

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

  • cfdguru
    cfdguru New Altair Community Member
    edited July 2014

    Yes, you can use AcuProbe.

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