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An airplane is cruising at $50\,m/s$ at standard sea level in straight and level flight. The airplane has a wing area of $15\,m^2$ and a wing span of $10\,m$ , and has the maximum gross weight of $1000\,kg$ . The airfoil of the wing has lift slope of $0.102$ per degree and angle of attack at zero lift of $-2.5^{\circ}$ . Considering, $\tau = 0.1$ , find the angle of attack for the wing. Also, find the induced drag for the airplane, if span efficiency factor is $0.6$ .
on 12th August 2021 in Aeronautics.
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Kumar59
A finite wing has aspect ratio of $6$ and taper ratio of $0.8$ . The airfoil constituting this wing has a lift slope of $0.102$ per degree, and angle of attack at zero lift of $-1.2^{\circ}$ . Assuming that $\delta =\tau$ and equals approximately $0.03$ , find the coefficient of lift and induced drag coefficients for this wing at an angle of attack of $6^{\circ}$ .
on 11th August 2021 in Aeronautics.
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Worldtech
Find the total drag of an airplane flying at a velocity of $90\,m/s$ with $L/D$ ratio maximum. Airplane is weighing $23000\,N$ and has a wing area of $20\,m^2$ and an aspect ratio of $9$ .
on 3rd February 2021 in Aeronautics.
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Worldtech
An airplane having a weight of $10,000 N$ is flying at a velocity of $260\,km/h$ at standard sea level conditions. Find the induced drag, if the wing of the airplane has an area of $16\,m^2$ and has an aspect ratio of $7.4$ .
on 3rd February 2021 in Flight mechanics.
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