incompressible flow Archives - Page 2 of 5

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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.
on 9th November 2019 in Aerodynamics.
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Worldtech
Starting with the definition of circulation, derive Kelvin’s circulation theorem.
on 9th November 2019 in Aerodynamics.
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Worldtech
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?
on 8th November 2019 in Aerodynamics.
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Worldtech
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 $2 ft$ .
on 8th November 2019 in Aerodynamics.
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Worldtech
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.
- incompressible flow
on 5th November 2019 in Aerodynamics.
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techAir
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.
- incompressible flow
on 5th November 2019 in Aerodynamics.
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techAir
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.
- incompressible flow
on 4th November 2019 in Aerodynamics.
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Worldtech
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.
- incompressible flow
on 4th November 2019 in Aerodynamics.
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techAir
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.
- incompressible flow
on 4th November 2019 in Aerodynamics.
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Worldtech
Derive the velocity potential for a doublet.
- incompressible flow
on 4th November 2019 in Aerodynamics.
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