
Consider an incompressible twodimensional viscous flow over a curved surface .Let the pressure distribution on the surface be \(p(s)=2+sin\left ( …
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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 …
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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}} …
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For the NACA \(2412\) airfoil, the lift coefficient and moment coefficient about the quarterchord at \(−6 ^{\circ}\) angle of attack …
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Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift …
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Starting with the definition of circulation, derive Kelvin’s circulation theorem.
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Consider an NACA \(2412\) airfoil with a \(2\;m\) chord in an airstream with a velocity of \(50\; m/s\) at standard …
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Consider the data for the NACA \(2412\) airfoil. Calculate the lift and moment about the quarter chord (per unit span) …
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Assume for a given airplane that the total length for the vertical struts (summed together) is \(25\; ft\), and that …
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The lift on a spinning circular cylinder in a freestream with a velocity of \(30 \;m/s\) and at standard sea …
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