
Find the coefficient of pressure at a point on the wing where the velocity is \(58\,m/s\). The airplane is flying …
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Calculate the pressure coefficient at a point on the airfoil where the pressure is \( 8.9 \times 10^4\,N/m^2\). Airfoil is …
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Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
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What is the difference between symmetrical and asymmetrical /cambered airfoil ?
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Define airfoil terminology and NACA series of airfoil nomenclature.
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What is flaps and what are they used for ?
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Stall in an aircraft occurs when there is a flow separation and reduction in the lift coefficient of the airfoil. …
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What is critical Mach number ?
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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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