Brian,

Lift=Cl*1/2*q*V^2*area
Drag=Cd*1/2*V^2*area

Cl is the lift coeff.
q is the density
(Imperial units q=.002378 slugs per qubic foot at sea level, metric units q=1.225 Kg per qubic meter at sea level)
V=velocity
Area=wing area

Example:

If a plane with a wing area of 4 sqft, at 30 fps velocity, at standard density .002378, Cl of 1 then,

Lift=1*1/2*.002378*30^2*4
Lift=1/2*.002378*900*4
Lift=4.28 pounds

To find Cl given Velocity:

CL=Lift/(1/2*q*V^2*area) Lift=Weight and weight/area= wingload so:
Cl=Wingload/(1/2*q*V^2) or
Cl= (2*wingload)/(q*V^2)

same example will say plane weight is five pounds:
Cl= (2*(5/4)/(.002378*30^2)
Cl=2.5/2.14
Cl=1.17

The induced drag= Cl^2/(pi*AR*e) AR=aspect ratio and e=oswald eff factor.

Here is a sight that you can calculated the air density for your conditions:

[link]http://wahiduddin.net/calc/calc_da.htm[/link]

Here a good site for more info:
[link]http://142.26.194.131/aerodynamics1/[/link]

Steve