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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 gliding distance of an aircraft flying at an altitude of $1500\,m$ with a maximum lift to drag ratio of $8$ .
Find the gliding distance of an aircraft flying at an altitude of $1500\,m$ with a maximum lift to drag ratio …
Airplane design

drag force

lift and drag

lift force

techAir Asked on 3rd February 2021 in Aeronautics.
- 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.
- 976 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
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 $50\,m/s$ .
Find the coefficient of pressure at a point on the wing where the velocity is $58\,m/s$ . The airplane is flying …
Aircraft performance

airfoil

Airplane design

Kumar59 Asked on 14th January 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
Calculate the pressure coefficient at a point on the airfoil where the pressure is $8.9 \times 10^4\,N/m^2$ . Airfoil is in freestream velocity of $40\,m/s$ and is at standard sea – level conditions.
Calculate the pressure coefficient at a point on the airfoil where the pressure is $8.9 \times 10^4\,N/m^2$ . Airfoil is …
Aircraft performance

airfoil

Airplane design

Kisan Kumar Asked on 12th January 2021 in Aeronautics.
- 2K views
- 1 answers
- 0 votes
Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an angle of attack of ${7\, ^ \circ }$ with a flow velocity of $40\, m/s$ at standard sea level conditions. The airfoil has a chord length of $1\, m$ .
Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
Aircraft performance

airfoil

Airplane design

airspeed

lift and drag

Kumar59 Asked on 4th January 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes

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