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An airfoil is in airflow with $0.52$ free stream Mach number. Local Mach number at a given point is $0.82$ . Find the pressure coefficient at this point.
An airfoil is in airflow with $0.52$ free stream Mach number. Local Mach number at a given point is $0.82$ . …
airfoil

airspeed

Compressible flow

Mach number

Worldtech Asked on 13th January 2022 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 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

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