An aircraft is traveling at 295 kts Sea level standard condi

An aircraft is traveling at 295 kts.

Sea level standard conditions.

Wing area is 500 ft^2.

The coefficient of drag is 0.016.

Calculate the drag on the airplane.

Solution

solution : given A = 500ft² = 46.4515 m²

V = 295kts = 151.761m/s

C_d= 0.016

AND standard sea level conditions density d= 1.225kg/m³

Drag D = 0.5*C_d*v² *A*d

=0.5*0.016*(151.761)²*46.4515*1.225

=10484.4627N =2357.0009Pounds