The aerodynamic force acting on a solid body can be expressed by a general equation:
F = [tex]1/2 \rho V^2 S C[/tex]
C is a force coefficient (either lift Cl, drag Cd or Cx, or whatever you're looking for)
S is a reference area (either frontal area, wing area for airplanes etc.)
The problem lies in the coefficient C. It depends on some adimensional numbers (Mach number and Reynolds number in most cases) and is usualy measured in a wind tunnel on a scaled model of the object.
If you were able to measure the force acting on the solid body, and if you knew the value of the aerodynamic coefficient C, then you wuld be also able to calculate the velocity from the formula above.
If you only knew the values of C vs. V (through Reynolds number) then it would necessarily be an iterative process, since you would have to estimate an initial V, then you would calculate C for that V, then you would recalculate V with that value of C, and then recalculate C with the new value of V, and so on and so on and so on... till the convergence of the result. :zzz:
On the other hand, if you had data (from real-scale or wind-tunnel measurements) which relate directly F to V (usually for incompressible flows and near-standard temperatures) then the process is straightforward: measure F --> read V from the F-V curve.
As mentiond the pitot-static tube measures wind velocity, and does so via comparason of the pressure (force per unit area) in 2chambers connected to tubes, one that face into the wind and and one perpendicular to the wind.