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Consider an incompressible two-dimensional viscous flow over a curved surface .Let the pressure distribution on the surface be $$p(s)=2+sin\left ( … Asked on 30th December 2019 in • 247 views • 1 answers • 0 votes • Calculate the lift and induced drag coefficients for the wing at a geometric angle of attack = \(7^{\circ}$$.

The measured lift slope for the NACA $$23012$$ airfoil is $$0.1080\; degree^{−1}$$, and $$α_{L}=0 = −1.3^{\circ}$$. Consider a finite wing …

Asked on 12th November 2019 in
• 308 views
• Using thin airfoil theory, calculate $$(a) α_{ L=0}$$ (b) $$cl$$ when $$α = 3^{\circ}$$.

The NACA 4412 airfoil has a mean camber line given by\[\frac{z}{c} = \left\{ {\begin{array}{*{20}{c}} {0.25\left[ {0.8\frac{x}{c} – {{\left( {\frac{x}{c}} \right)}^2}} …

Asked on 11th November 2019 in
• 657 views
• Calculate the location of the aerodynamic center.

For the NACA $$2412$$ airfoil, the lift coefficient and moment coefficient about the quarter-chord at $$−6 ^{\circ}$$ angle of attack …

Asked on 10th November 2019 in
• 187 views
• Calculate the lift coefficient and the moment coefficient about the leading edge.

Consider a thin, symmetric airfoil at $$1.5^{\circ}$$ angle of attack. From the results of thin airfoil theory, calculate the lift …

Asked on 9th November 2019 in
• 195 views
• Starting with the definition of circulation, derive Kelvin’s circulation theorem.

Starting with the definition of circulation, derive Kelvin’s circulation theorem.

Asked on 9th November 2019 in
• 189 views
• what is the angle of attack?

Consider an NACA $$2412$$ airfoil with a $$2\;m$$ chord in an airstream with a velocity of $$50\; m/s$$ at standard …

Asked on 8th November 2019 in
• 193 views
• Calculate the lift and moment about the quarter chord (per unit span) for this airfoil.

Consider the data for the NACA $$2412$$ airfoil. Calculate the lift and moment about the quarter chord (per unit span) …

Asked on 8th November 2019 in
• 301 views
• Calculate the drag (in pounds) contributed by the struts and bracing wires when the airplane is flying at $$120 \;mi/h$$ at standard sea level.

Assume for a given airplane that the total length for the vertical struts (summed together) is $$25\; ft$$, and that …

Asked on 5th November 2019 in
• 169 views
The lift on a spinning circular cylinder in a freestream with a velocity of $$30 \;m/s$$ and at standard sea …