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• ## How urban air mobility work?

on 13th December 2021 in Aeronautics.
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• ## What are form drag and profile drag?

on 8th September 2021 in Aeronautics.
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• ## A finite wing with an elliptical lift distribution has an aspect ratio of $$6$$. The airfoil of the wing has a lift slope of $$0.15$$ per degree. Find and compare the lift slopes for a straight wing and a swept wing with a half-chord line sweep of $$30^{\circ}$$.

on 12th August 2021 in Aeronautics.
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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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• ## 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.
• 493
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• ## A NACA 0012 airfoil having a chord of $$2.3\,m$$ is in an airstream velocity of $$70\,m/s$$ at standard sea level conditions. Find the angle of attack for this airfoil,  if the lift per unit span produced is $$1400\,N$$.

on 22nd July 2021 in Aeronautics.
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• ## Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has an inlet -to-throat area ratio of $$10$$. The U-tube mercury manometer read as a height difference of $$10.5\,cm$$ for the pressure difference between the inlet and the test section of the wind tunnel.

on 15th June 2021 in Aeronautics.
• 590
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• ## Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ in a Mach $$3$$ flow.

on 26th March 2021 in Aeronautics.
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• ## Find the gliding distance of an aircraft flying at an altitude of $$1500\,m$$ with a maximum lift to drag ratio of $$8$$.

on 3rd February 2021 in Aeronautics.
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• ## 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.
• 590
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