• Question Tag: airfoil
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• ## 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 $$0.82$$. …

Asked on 13th January 2022 in
• 304 views
• ## 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 …

Asked on 12th August 2021 in
• 385 views
• ## 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 …

Asked on 12th August 2021 in
• 366 views
• ## 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 …

Asked on 11th August 2021 in
• 363 views
• ## 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 …

Asked on 22nd July 2021 in
• 485 views
• ## 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. …

Asked on 22nd July 2021 in
• 630 views
• ## 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 …

Asked on 22nd July 2021 in
• 521 views
• ## 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. …

Asked on 13th July 2021 in
• 1K views
• ## Find the coefficient of pressure at a point on the wing.

Find the coefficient of pressure at a point on the wing where the velocity is $$58\,m/s$$. The airplane is flying …

Asked on 14th January 2021 in
• 691 views
Calculate the pressure coefficient at a point on the airfoil where the pressure is $$8.9 \times 10^4\,N/m^2$$. Airfoil is …