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The Cessna Cardinal, a single-engine light airplane, has a wing with an area of 16.2 m2 and an aspect ratio of 7.31. Assume that the span efficiency factor is 0.62.
The Cessna Cardinal, a single-engine light airplane, has a wing with an area of 16.2 m2 and an aspect ratio …
Aircraft performance

Airplane design

flight mechanics

Worldtech Asked on 17th December 2024 in Flight mechanics.
- 207 views
- 1 answers
- 0 votes
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.
For a given set of free-stream conditions and angle of attack, the lift per unit span for a given airfoil …
Aircraft performance

Airplane design

airspeed

Worldtech Asked on 9th November 2023 in Flight mechanics.
- 649 views
- 1 answers
- 0 votes
What are the roles of ailerons and flaps in an aircraft?
What are the roles of ailerons and flaps in an aircraft?
Aircraft performance

Kumar59 Asked on 7th September 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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 $0.36$ .
Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( …
Aircraft performance

Airplane design

Worldtech Asked on 12th February 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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.
Consider wing-body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of moment …
Aircraft performance

Airplane design

techAir Asked on 12th February 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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.
Find the turn radius and turn rate of an airplane, flying at a velocity of $403.2\, km/h$ and has a …
Aircraft performance

Airplane design

Worldtech Asked on 3rd February 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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 $8000\,N$ .
Find the stalling speed of an airplane which has a wing area of $17\,m^2$ and is flying at sea level …
Aircraft performance

Airplane design

airspeed

Stall

techAir Asked on 3rd February 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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 $7.4$ .
An airplane having a weight of $10,000 N$ is flying at a velocity of $260\,km/h$ at standard sea level conditions. …
Airplane design

drag

drag force

Induced drag

Worldtech Asked on 3rd February 2021 in Flight mechanics.
- 969 views
- 1 answers
- 0 votes
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?
An airplane flying at a Mach number of 2.2 makes a Mach wave at the nose. What angle does it …
Mach number

Mach wave

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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.
The velocity at a point on the wing placed in a wind tunnel is $251 m/s$ . The pressure and temperature …
Aircraft performance

Airplane design

flight mechanics

Kisan Kumar Asked on 14th January 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes

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