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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
All the factors remaining constant, if the weight of an aircraft increases by \(30 \%\) then the take off distance will increase by approximately.
All the factors remaining constant, if the weight of an aircraft increases by \(30 \%\) then the take off distance …
Aircraft performance

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take-off distance

Kisan Kumar Asked on 10th November 2019 in Flight mechanics.
- 1K 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
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.
- 1K 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

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