Calculate the density at which the available thrust of a jet propelled aeroplane is equal to the minimum drag for the full fuel load case. Use the simplest assumption for the variation of engine thrust with density.(adsbygoogle = window.adsbygoogle || []).push({});

Wing area, S = 29.5

Weight, W = 88000

C_{D,0}= 0.02

k = 0.044

Max thrust (at sea level) = 16000N

C_{T}= 1.7*10^-4

I use the formula Dmin = 2((C_{D,0}*k)^0.5)*W = 5221N

The problem I have is that I can't work out the density without the velocity but there is no way to relate velocity to drag without density. Where do I go from here?

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# Calculate the density at which the available thrust is equal to the minimum drag

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