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Consider an incompressible two-dimensional viscous flow over a curved surface. Let the pressure distribution on the surface be \(p(s)=2+sin\left ( \frac{\pi}{2}+s \right )\;N/m^2\),where \(s\) is the distance along the curved surface from the leading edge. Find the distance from where the flow separates.
Consider an incompressible two-dimensional viscous flow over a curved surface. Let the pressure distribution on the surface be \(p(s)=2+sin\left ( …
GATE

incompressible flow

Kisan Kumar Asked on 30th December 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Consider the superposition of a uniform flow 29 m/s, a source of strength 50m^2/s and a sink of strength –50m^2/s. The distance between the source and sink is 2m. Find the slenderness ratio of the Rankine oval, that is the ratio of the horizontal and vertical lengths for an oval shape.
Consider the superposition of a uniform flow 29 m/s, a source of strength 50 m^2/s and a sink of strength …
Aero Student Asked on 13th December 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Show the stagnation points
The lift coefficient on a spinning circular cylinder in a freestream with a velocity of 24 and at an altitude …
Aero Student Asked on 13th December 2019 in Aerodynamics.
- 1K views
- 0 answers
- 0 votes
Using thin airfoil theory, calculate \( (a) α_{ L=0}\) (b) \(cl\) when \(α = 3^{\circ} \).
The NACA 4412 airfoil has a mean camber line given by\[\frac{z}{c} = \left\{ {\begin{array}{*{20}{c}} {0.25\left[ {0.8\frac{x}{c} – {{\left( {\frac{x}{c}} \right)}^2}} …
airfoil

Airplane design

incompressible flow

Worldtech Asked on 11th November 2019 in Aerodynamics.
- 4K views
- 1 answers
- 0 votes
For the NACA \(2412\) airfoil, the lift coefficient and moment coefficient about the quarter-chord at \(−6 ^{\circ}\) angle of attack are \(−0.39\) and \(−0.045\),respectively. At \(4^{\circ}\) angle of attack, these coefficients are \(0.65\) and \(−0.037\),respectively. Calculate the location of the aerodynamic center.
For the NACA \(2412\) airfoil, the lift coefficient and moment coefficient about the quarter-chord at \(−6 ^{\circ}\) angle of attack …
aerodynamic center

airfoil

incompressible flow

Worldtech Asked on 10th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
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
- 0 votes
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.
- 1K 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

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