When an aircraft is descending is left reduced and drag increased, please can some check my figures. :)? this1

Question

When an aircraft is descending is left reduced and drag increased, please can some check my figures. :)?
a340 at -2degrees angle of attack
wing area 5825ft squared
density ratio= 0.5328
speed 435knots
altitude; 20,000ft
I worked lift out to be
Lift = -559,819.26 pounds
and drag to be
Drag = 43,797.82 pounds

do these sound right, if not can you tell me how to do the coefficient for descening of an aircraft for the values of lift and drag??

Answer 1

I'm troubled by your negative lift, since that implies that the plane is being pulled downward.

Lift should be positive, should it not?

The wing area doesn't correspond to even the largest A340 (4729 ft^2):
http://www.airbus.com/en/aircraftfamilies/a330a340/a340-600/specifications.html
but you can see that the A340-600 weighs over 800 klb, so 560 klbs of lift is a bit low for that much wing area.

Are you using C*rho*((v^2)/2)*area? What are you using for the coefficient of lift?