Flight mechanics Archives - Aerospace answers

Worldtech
For a given set of free-stream conditions and angle of attack, the lift per unit span for a given airfoil is 200 pounds per foot (lb/ft). The location of the center of pressure is at 0.3c, where c is the chord length; c = 5 ft.
on 9th November 2023 in Flight mechanics.
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Kumar59
What are the roles of ailerons and flaps in an aircraft?
- Aircraft performance
on 7th September 2021 in Flight mechanics.
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Worldtech
Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( 0.3\) chord length, the location of center of gravity is at \(0.38\) chord length, tail volume ratio is \(0.352\), tail lift slope is \(0.12\) per degree, lift slope of the wing body is \(0.085\) per degree and \(\frac{{\partial \varepsilon }}{{\partial \alpha }}\) from wind tunnel data is \(0.36\).
- Aircraft performance
- Airplane design
on 12th February 2021 in Flight mechanics.
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techAir
Consider wing-body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of moment about the center of gravity and the coefficient of moment about aerodynamic center is \(0.006\) and \(-0.015\). Aerodynamic center is forward of the center of gravity at \(0.035\) chord length.
- Aircraft performance
- Airplane design
on 12th February 2021 in Flight mechanics.
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Worldtech
Find the turn radius and turn rate of an airplane, flying at a velocity of \(403.2\, km/h\) and has a lift coefficient of \(1.3\). Airplane has a wing area of \(48\,m^2\) and weighs \(100,000\,N\), and is flying at sea level.
- Aircraft performance
- Airplane design
on 3rd February 2021 in Flight mechanics.
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techAir
Find the stalling speed of an airplane which has a wing area of \(17\,m^2\) and is flying at sea level with maximum lift coefficient of \(2.2\), flaps down. Weight of the airplane is \(8000\,N\).
on 3rd February 2021 in Flight mechanics.
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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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Kumar59
An airplane flying at a Mach number of 2.2 makes a Mach wave at the nose. What angle does it make with the flow direction?
on 18th January 2021 in Flight mechanics.
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Kisan Kumar
The velocity at a point on the wing placed in a wind tunnel is \(251 m/s\). The pressure and temperature of the test section is \(1\,atm\) and \(285\,K\). If the velocity of the flow in the test section is \(235\;m/s\), find the pressure coefficient at the point.
on 14th January 2021 in Flight mechanics.
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Kumar59
Find the coefficient of pressure at a point on the wing where the velocity is \(58\,m/s\). The airplane is flying at a low speed of \(50\,m/s\).
on 14th January 2021 in Flight mechanics.
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