
An airfoil is in airflow with \(0.52\) free stream Mach number. Local Mach number at a given point is \(0.82\). …
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A finite wing with an elliptical lift distribution has an aspect ratio of \(6\). The airfoil of the wing has …
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An airplane is cruising at \(50\,m/s\) at standard sea level in straight and level flight. The airplane has a wing …
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A finite wing has aspect ratio of \(6\) and taper ratio of \(0.8\). The airfoil constituting this wing has a …
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A NACA 4421 airfoil having a chord length of \(2\,m\) is flying at an velocity of \(70\,m/s\) at an altitude …
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An airfoil has a lift coefficient and moment coefficient of \(0.35\) and \(0.050\) about quarterchord at \(6^{\circ}\) angle of attack. …
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A NACA 0012 airfoil having a chord of \(2.3\,m\) is in an airstream velocity of \(70\,m/s\) at standard sea level …
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A positively cambered airfoil has a zerolift angle of \(3.5^{\circ}\). The lift slope for this airfoil is \(0.12\) per degree. …
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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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