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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 coefficient and the moment coefficient about the leading edge.
Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift …
airfoil

Airplane design

incompressible flow

techAir Asked on 9th November 2019 in Aerodynamics.
- 2K views
- 1 answers
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Starting with the definition of circulation, derive Kelvin’s circulation theorem.
Starting with the definition of circulation, derive Kelvin’s circulation theorem.
airfoil

Airplane design

incompressible flow

Worldtech Asked on 9th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Consider an NACA \(2412\) airfoil with a \(2\;m\) chord in an airstream with a velocity of \(50\; m/s\) at standard sea level conditions. If the lift per unit span is \(1353\; N\), what is the angle of attack?
Consider an NACA \(2412\) airfoil with a \(2\;m\) chord in an airstream with a velocity of \(50\; m/s\) at standard …
Aircraft performance

airfoil

Airplane design

incompressible flow

Worldtech Asked on 8th November 2019 in Aerodynamics.
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- 1 answers
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Consider the data for the NACA \(2412\) airfoil. Calculate the lift and moment about the quarter chord (per unit span) for this airfoil when the angle of attack is \(4^{\circ}\) and the freestream is at standard sea level conditions with a velocity of \(50 ft/s\). The chord of the airfoil is \(2 ft\).
Consider the data for the NACA \(2412\) airfoil. Calculate the lift and moment about the quarter chord (per unit span) …
Aircraft performance

airfoil

Airplane design

incompressible flow

Worldtech Asked on 8th November 2019 in Aerodynamics.
- 4K views
- 1 answers
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A typical World War I biplane fighter (such as the French SPAD shown in Figure 3.50) has a number of vertical interwing struts and diagonal bracing wires. Assume for a given airplane that the total length for the vertical struts (summed together) is 25ft, and that the struts are cylindrical with a diameter of 2 in. Calculate the drag (in pounds) contributed by the struts and bracing wires when the airplane is flying at \(120 \;mi/h\) at standard sea level.
Assume for a given airplane that the total length for the vertical struts (summed together) is \(25\; ft\), and that …
incompressible flow

Worldtech Asked on 5th November 2019 in Aerodynamics.
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- 1 answers
- 0 votes
The lift on a spinning circular cylinder in a freestream with a velocity of \(30 \;m/s\) and at standard sea level conditions is \(6\; N/m\) of span. Calculate the circulation around the cylinder.
The lift on a spinning circular cylinder in a freestream with a velocity of \(30 \;m/s\) and at standard sea …
incompressible flow

techAir Asked on 5th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Consider the lifting flow over a circular cylinder of a given radius and with a given circulation. If \(V_{\infty}\) is doubled, keeping the circulation the same, does the shape of the streamlines change? Explain.
Consider the lifting flow over a circular cylinder of a given radius and with a given circulation. If \(V_{\infty}\) is …
incompressible flow

techAir Asked on 4th November 2019 in Aerodynamics.
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- 1 answers
- 0 votes
Consider the nonlifting flow over a circular cylinder of a given radius, where \(V_{\infty} = 20\; ft/s\). If \(V_{\infty}\) is doubled, that is, \(V_{\infty} = 40 ft/s\), does the shape of the streamlines change? Explain.
Consider the nonlifting flow over a circular cylinder of a given radius, where \(V_{\infty} = 20 ft/s\). If \(V_{\infty}\) is …
incompressible flow

Worldtech Asked on 4th November 2019 in Aerodynamics.
- 4K views
- 1 answers
- 0 votes
Consider the nonlifting flow over a circular cylinder. Derive an expression for the pressure coefficient at an arbitrary point \((r, θ)\) in this flow, and show that it reduces to Equation \(Cp = 1 − 4 sin^{2} θ\) on the surface of the cylinder.
Consider the nonlifting flow over a circular cylinder. Derive an expression for the pressure coefficient at an arbitrary point \((r, …
incompressible flow

techAir Asked on 4th November 2019 in Aerodynamics.
- 4K views
- 1 answers
- 0 votes
Derive the velocity potential for a doublet.
Derive the velocity potential for a doublet.
incompressible flow

Worldtech Asked on 4th November 2019 in Aerodynamics.
- 3K views
- 1 answers
- 0 votes

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