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Old   March 4, 2004, 04:37
Default Problem in calculating drag coefficient
Sohail Ahmed
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I am a beginner in using Fluent. Please help me out to calculate the drag and friction coefficients over an aerodynamic body, if I have the results of pressure, temperature and velocity profiles.
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Old   March 4, 2004, 12:55
Default Re: Problem in calculating drag coefficient
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Well its not difficult:

go to report-forces and give the direction vector...for example give 1 for x and 0 for y and 0 for z (3d)....that will be axial force.

Similarly x=0, y=1 and z=0 is Normal force....

In this way for Lift and drag for a body at 10 deg AOA give components as x= cos(10)n y=sin(10).

fluent will automatically report the forces and moments for you.

I hope this solves your problem

Further you might find it helpful to look at the 2nd tutorial in fluent which is modelling external compressible flow on an aerofoil..

Regards Farooq
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Old   March 18, 2004, 01:40
Default Re: Problem in calculating drag coefficient
Sohail Ahmed
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Thanks Farooq! Can u please help me in defining boundary conditions in a duct flow?

Currently I am defining Inlet Static Temp and Inlet velocity. No condition defined at the outlet boundary. Also, where should I define Inlet Pressure? Does it have to be defined as "Operating Condition", giving the x & y coordinates of the location (inlet / outlet etc.) or it should be defined in " Boundary Conditions", or while I initialize the problem?

Also, please advise whether the solution has to be 'computed from' Inlet Velocity Zone or from 'All Zones'?

Please help! Thanks
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