Hi, I have a project underway to calculate the rates of climb of airliners based on various factual information about the airfoil.

This includes calculating the lift quantity and induced drag in pounds. Thew following data will go into a spreadsheet, you see, and these are the requirements:

The input example below is of a generic aircraft.

INPUT

AIRFOIL

Wing Area: 980sq/ft

Mean Chord: 11.06ft

Wing Span: 88.6ft

Aspect Ratio: 8.01

Camber - %C: 4.05

Thickness - %crd: 9.25

OUTPUT REQUIRED

Total lift at a given airspeed (lbs) at sea level

Induced drag at a given airspeed (lbs) at sea level

AIRCRAFT INPUT

Gross takeoff weight: 107,456lbs

Gross Thrust: 25,120lbs

Parasite Drag

OUTPUT desired:

Some form of calculation that gives me the rate of climb based on the excess thrust/lift taking into account drag levels and aircraft weight.

Is this asking too much maybe? I know there are many "experts" in this area on the board, so I'd be happy to know a way of calculating these parameters to give me some intelligible data on Microsoft Excel.

That aircraft above is an example, with most of the data required to calculate this stuff, can anyone show me the formulas to create the lift/drag quantity and work out the rate of climb?