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An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft thrust is 46082.75N then determine aircraft drag.

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An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft thrust is 46082.75N then determine aircraft drag.

(a) 33898.64 N

(b) 52708.59 N

(c) 82814.78 N

(d) 8999.99 N

I got this question in final exam.

The query is from Cruising Performance in portion Cruising Performance of Aircraft Performance

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Correct option is (d) 8999.99 N

The explanation: Aircraft weight=mg=11000*9.81=107910 N.

Engine thrust: From equating the horizontal forces we get the following equation: Tcosα=D+Wsinγ

D=Tcosα-Wsinγ

D=46082.75*cos(5)–107910*sin(20)

D=8999.99 N.

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