Aeronautics Archives - Aerospace answers

techAir
How urban air mobility work?
- Airplane design
- flight mechanics
on 13th December 2021 in Aeronautics.
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Kumar59
What are form drag and profile drag?
on 8th September 2021 in Aeronautics.
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Worldtech
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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techAir
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.
- 493
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Worldtech
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 \(1400\,N\).
- airfoil
- airspeed
- lift
- lift coefficient
- lift force
on 22nd July 2021 in Aeronautics.
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Kisan Kumar
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.
- airspeed
- incompressible flow
on 15th June 2021 in Aeronautics.
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Kumar59
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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techAir
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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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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