If you have the capability to model and mesh a domain for your aircraft you can essentially proceed by following a tutorial for a 2D airfoil. This will provide the basis for setting angle of attack and outputting force vectors. The Cornell tutorials are great place to start:

https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+Flow+over+an+Airfoil-+Problem+Specification

I would suggest doing computations using a panel code first since they are much much faster. Full CFD solutions of an entire aircraft will be computationally expensive and it might be difficult to fully resolve all the boundary layer features necessary for an accurate prediction. XFLR5 is a useful code that might be easier if you are looking for preliminary results.

http://www.xflr5.com/xflr5.htm

Yes you can find it over fluent to explain hole thing over here is bit hard so i suggest you to go through some online available tutorials on air foil and learn the way then you ill able to get the answer of your problem.

Hello, you can find it and the procedure is you need to go in the report section-projected area in x-direction and then paste it in the area section in reference values. Then go back to report-forces and select the aircraft and this way you get drag.again go to report and put 1 in the box next to y direction and put o in the box next to y-direction and this way you get lift force.

Thank you very much for your answers.

I would like to ask further that if i find out the lift and drag coefficients from an airfoil of an aircraft, can I take these coefficients as that of the entire aircraft?I think the interference drag will be missing if i considered only the airfoil.Am i right?And will there be a big anomaly if the interference drag is not considered?

Yes , that will be missing but as we know it contribute very less in the total drag so that won't be a problem as per your validation concern.