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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.
- 969 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.
- 945 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.
- 918 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.
- 2K 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.
- 1K views
- 1 answers
- 0 votes

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