Question

a) For NACA 4412 airfoil (use Xfoil)(http://web.mit.edu/drela/Public/web/xfoil/) (use this software to see lift and drag characteristics at different angle of attack and Reynolds numbers) b) with chord of 1.5 m at an angle of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions, calculate the lift and drag per unit span. Note: The viscosity coefficient at standard sea-level conditions is $1.7894 \times 10^{-5} kg/(m \cdot s)$. calculate the lift-to-drag ratio. c) Consider a finite wing of aspect ratio 4 the angle of attack is 5°. Calculate (a) the lift coefficeint at low speeds (incompressible flow)

          a) For NACA 4412 airfoil (use Xfoil)(http://web.mit.edu/drela/Public/web/xfoil/)
(use this software to see lift and drag characteristics at different angle of attack
and Reynolds numbers)
b) with chord of 1.5 m at an angle
of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions,
calculate the lift and drag per unit span. Note: The viscosity coefficient at standard
sea-level conditions is $1.7894 \times 10^{-5} kg/(m \cdot s)$.
calculate the lift-to-drag ratio.
c) Consider a finite wing of aspect ratio 4
the angle of attack
is 5°. Calculate (a) the lift coefficeint at low speeds (incompressible flow)

a) For NACA 4412 airfoil (use Xfoil)(http://web.mit.edu/drela/Public/web/xfoil/)
(use this software to see lift and drag characteristics at different angle of attack
and Reynolds numbers)
b) with chord of 1.5 m at an angle
of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions,
calculate the lift and drag per unit span. Note: The viscosity coefficient at standard
sea-level conditions is 1.7894 × 10^-5 kg/(m · s).
calculate the lift-to-drag ratio.
c) Consider a finite wing of aspect ratio 4
the angle of attack
is 5°. Calculate (a) the lift coefficeint at low speeds (incompressible flow)

Added by Melanie G.

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