Lift and Drag Coefficients using load cell data I have a MAV and I need to find out the lift and drag coefficients for the wing and tail. I am not available with a wind tunnel so I will be using a load cell along with a separate wind source. Now I can measure forces on the MAV, airspeed at the wing and tail surfaces. 

If I just use the angle of attack at the centre of mass then I can find the corresponding lift and drag coefficients (since there are two unknowns and two equations for forces along x and z axis). Now if I want to find separate lift and drag coefficients for wing and tail, for the corresponding angle of attacks, how am I going to do that? Once again I have force on the MAV in the x and z axis, angle of attacks for wing and tail, air speed, two equations of forces but four unknowns.

Please guide me resolve this issue.
I guess your design is a conventional one.

One approach could be integrating two load cells in between the tail and wing sections.

You can measure drag force and moment. And the moment may help you estimate the tail lift (with some serious assumptions though).

If space is a concern, you can try building a scaled model (2:1?) to test a larger model. The resulting forces and moments must be corrected for Reynolds effects.