How to find the velocity of the air flow around the aerofoil?
U - freesteam velocity
β - angle of wing camber
The Attempt at a Solution
To find the velocity of the air flow at each section of the aerofoil, am I right to say that the horizontal velocity of the air flow is constant throughout the chord while the vertical component of the velocity varies along the chord depending on the angle of chord w.r.t. horizontal?
So velocity at first plane is U/cosβ? Subsequently, the velocity at the 2nd and 3rd plane will be U and U/cosδ respectively?
If that is the case, will shifting the air upwards, not push the wing down? Or am I right to say that as the airflow around the wings, there is no net upward motion of air, thus it does not push the wing downwards?
26.3 KB Views: 472