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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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- 0 votes
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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. …
- 25 views
- 1 answers
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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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- 1 answers
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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. …
- 51 views
- 1 answers
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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 …
- 75 views
- 1 answers
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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 …
- 72 views
- 1 answers
- 0 votes
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A pitot tube of an airplane which is flying at an standard sea level measures a pressure of \(1.09 \times …
- 71 views
- 1 answers
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Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …
- 91 views
- 1 answers
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A venturi is attached on a side of an airplane fuselage, has an throat to inlet area ratio of \(0.8\). …
- 82 views
- 1 answers
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In a flow field, the velocity components are, \(u=\left ( 6x^{2}y+t \right ),v=\left ( 3yx+t^{2}+3 \right )\) and \( w=\left …
- 212 views
- 1 answers
- 0 votes
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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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