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direction vectors for lift and drag for 3d wing

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Old   July 3, 2014, 13:55
Default direction vectors for lift and drag for 3d wing
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in 2d aerofoil analysis the direction vectors of aoa are used to calculate lift and drag does the same hold good for 3d wing also? moreover for lift calculation a different area is required while for dag calculation a different area is required shud both be calculated separately in fluent?
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Old   July 4, 2014, 05:50
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in 2d aerofoil analysis the direction vectors of aoa are used to calculate lift and drag does the same hold good for 3d wing also? moreover for lift calculation a different area is required while for dag calculation a different area is required shud both be calculated separately in fluent?

For both lift and drag calculations use the projected area of your wing (projected in global roll and pitch axis (x-y)).
In Fluent you can specify your wing area in the Reference Values Tab and monitor your coefficients. Once you have coefficients you can calculate the force.
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Old   July 4, 2014, 05:53
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mean if my geometry is in YZ plane then i have to take projected area of x axis and z axis add them and use them as reference?
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Old   July 4, 2014, 06:20
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mean if my geometry is in YZ plane then i have to take projected area of x axis and z axis add them and use them as reference?
Without a picture no one can answer you.
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Old   July 4, 2014, 06:27
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uploaded the foto
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Old   July 4, 2014, 06:44
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Use the projected area of your wing in the x-y-plane to build coefficients.
But if you just want to calculate forces you can also use the Reports Tab in Fluent (no wing area required). Just specify a direction vector and your parts / surfaces and Fluent will calculate the forces you want to know.
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Old   July 4, 2014, 06:47
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sir flow direction is in y and z direction so should i use the z axis projected area and x axis projected or x and y axis?
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Old   July 4, 2014, 07:02
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I have absolutely no idea what you are trying to do - its not possible to project an area to an axis. You have to project the area to a plane - in your system to the xy plane (the plane normal to your z-axis).
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Old   July 4, 2014, 07:12
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sir i am trying to calculate lift and drag coefficient for this configuration at mach 0.8 and 41000 feet altitude (cruise condition) i am using fluent in fluent i can find projected area in axis not in plane i hope i have made myself clear
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Old   July 4, 2014, 07:22
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ok. your first post says you want to calculate forces and not coefficients.
use the projection direction z-axis. this will give you the projected area in the xy-plane you need for the coefficients.
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