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A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At the top of the sphere there is a pressure tap which is connected by a tube to one side of a manometer. There is a pressure tap on the surface of the cylinder which is connected to the other side of the manometer. Find the location of this tap on cylindrical surface such that there is no deflection of fluid in the manometer.
A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At …
fluids

incompressible flow

Kisan Kumar Asked on 1st September 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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 $30^{\circ}$ .
A finite wing with an elliptical lift distribution has an aspect ratio of $6$ . The airfoil of the wing has …
airfoil

lift coefficient

swept wing

Worldtech Asked on 12th August 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
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 $0.6$ .
An airplane is cruising at $50\,m/s$ at standard sea level in straight and level flight. The airplane has a wing …
Aircraft performance

airfoil

Induced drag

techAir Asked on 12th August 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
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 $6^{\circ}$ .
A finite wing has aspect ratio of $6$ and taper ratio of $0.8$ . The airfoil constituting this wing has a …
airfoil

Induced drag

lift coefficient

Kumar59 Asked on 11th August 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
A NACA 4421 airfoil having a chord length of $2\,m$ is flying at an velocity of $70\,m/s$ at an altitude of $2\,km$ . Find the lift per unit span and the circulation at an angle of attack of $4^{\circ}$ , for this airfoil.
A NACA 4421 airfoil having a chord length of $2\,m$ is flying at an velocity of $70\,m/s$ at an altitude …
airfoil

airspeed

Circulation

lift coefficient

Kisan Kumar Asked on 22nd July 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
An airfoil has a lift coefficient and moment coefficient of $-0.35$ and $-0.050$ about quarter-chord at $-6^{\circ}$ angle of attack. The airfoil has lift coefficient and moment coefficient of $0.70$ and $-0.040$ at an angle of attack of $4^{\circ}$ about the same quarter chord. Find the location of the aerodynamic center.
An airfoil has a lift coefficient and moment coefficient of $-0.35$ and $-0.050$ about quarter-chord at $-6^{\circ}$ angle of attack. …
aerodynamic center

airfoil

lift coefficient

techAir Asked on 22nd July 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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 $1400\,N$ .
A NACA 0012 airfoil having a chord of $2.3\,m$ is in an airstream velocity of $70\,m/s$ at standard sea level …
airfoil

airspeed

lift

lift coefficient

lift force

Worldtech Asked on 22nd July 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
Can an airfoil fly upside-down ?
A positively cambered airfoil has a zero-lift angle of $-3.5^{\circ}$ . The lift slope for this airfoil is $0.12$ per degree. …
airfoil

lift

lift and drag

lift coefficient

lift force

Kisan Kumar Asked on 13th July 2021 in Aerodynamics.
- 3K views
- 1 answers
- 0 votes
Find the circulation around a spinning circular cylinder in free stream flow of velocity $40\,m/s$ at a standard sea level conditions, if the lift produced by the cylinder is $8\,N/m$ of span.
Find the circulation around a spinning circular cylinder in free stream flow of velocity $40\,m/s$ at a standard sea level …
Circulation

lift

Kumar59 Asked on 16th June 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
An airplane is flying at an velocity of $100\,m/s$ . Find the pressure coefficient at a point on the surface of the wing where the flow velocity is $140\,m/s$ .
An airplane is flying at an velocity of $100\,m/s$ . Find the pressure coefficient at a point on the surface of …
Aircraft performance

Airplane design

airspeed

Worldtech Asked on 16th June 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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