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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.
- 2K views
- 1 answers
- 0 votes
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
- 0 votes
Write a matlab code for conformal mapping of a circle to an airfoil.
Write a matlab code for conformal mapping of a circle to an airfoil.
Matlab

Worldtech Asked on 6th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Write a matlab code for streamline flow around a cylinder.
Write a matlab code to plot streamline flow around a cylinder.
Matlab

Worldtech Asked on 6th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Write a matlab solution to Rankine nose problem.
Write a matlab solution to Rankine nose problem.
Matlab

techAir Asked on 5th November 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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.
- 2K views
- 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.
- 2K views
- 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.
- 5K 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

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