i am having trouble calculating various drag co-efficents for a dc -10 in cruise.(adsbygoogle = window.adsbygoogle || []).push({});

i have found this data:

Thrust: 153000 lb

density: 0.00085 slug/ft

V= 852ft/s

W=580000lb

AR= 7.5

e= .8

S= 3958ft^2

Cl= 0.5

I have also found the formulas

Cd= D/ (density x S x V^2 /2)

Cd= Cdo + ((cl^2) / (pi x AR x e))

Cdi= (cl^2)/ (pi x AR x e)

i have tried these but get odd answers. i need help to know whether my mistake is my data, my formulas or my calculation.

help with graphing this data vs airspeed would also be appriciated

cheers

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# Calculating drag

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