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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 …
- 24 views
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An airfoil has a lift coefficient and moment coefficient of \(-0.35\) and \(-0.050\) about quarter-chord 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 zero-lift 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 …
- 226 views
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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 …
- 289 views
- 1 answers
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Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
- 202 views
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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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Question Tag: airfoil
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LATEST QUESTIONS
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Find the location of the aerodynamic center.
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Find the angle of attack for this airfoil, if the lift per unit span produced is \(1400\,N\).
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Can an airfoil fly upside-down ?
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Find the circulation around a spinning circular cylinder in free stream flow of velocity \(40\,m/s\) at a standard sea level conditions, if the lift produced by the cylinder is \(8\,N/m\) of span.
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An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of the wing where the flow velocity is \(140\,m/s\).
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