angel
04-11-2006, 08:04 AM
i need some help calculating the co-efficent of drag and lift in take-off/landings for a dc-10-30.
i have the formulas
cl = lift/ (density x V^2 x S)
Cd = drag / (density x S x V^2 / 2)
Cd = Cd0 + (( Cl^20) / (pi x AR x e)
cdi = (cl^2) / (pi x AR x e)
S= 3958
e= .8
AR= 7.5
density = sea level
i am unsure how to calculate the various coeffecients for both take off and landing as lift does not = weight and drag does not= thrust
i have the formulas
cl = lift/ (density x V^2 x S)
Cd = drag / (density x S x V^2 / 2)
Cd = Cd0 + (( Cl^20) / (pi x AR x e)
cdi = (cl^2) / (pi x AR x e)
S= 3958
e= .8
AR= 7.5
density = sea level
i am unsure how to calculate the various coeffecients for both take off and landing as lift does not = weight and drag does not= thrust