• Question Tag: lift coefficient
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• 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 …

Worldtech Asked on 12th August 2021 in
• 823 views
• 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 …

Kumar59 Asked on 11th August 2021 in
• 597 views
• 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 …

Kisan Kumar Asked on 22nd July 2021 in
• 796 views
• 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. …

techAir Asked on 22nd July 2021 in
• 911 views
• 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 …

Worldtech Asked on 22nd July 2021 in
• 747 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. …

Kisan Kumar Asked on 13th July 2021 in
• 2K views
• Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ in a Mach $$3$$ flow.

Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ …

Kumar59 Asked on 26th March 2021 in
• 708 views
• What are angle of attack, absolute angle of attack and induced angle of attack?

What are angle of attack, absolute angle of attack and induced angle of attack?

Kisan Kumar Asked on 4th January 2021 in
• 2K views