I understand what you mean that lift is due to the component of the airflow that flows perpendicular from LE-TE, but don't see how the spanwise flow could flow in-out since;
1) I thought that spanwise flow was due in part to the voticies that form at the tips, flowing bottom to top, which tend to push the upper surface air towards the root.
2) The lift formula, L=C
L1/2pV^2S
- The inboard section has a greater surface area (S)
-Flap causes a greater increase in camber at the root V
S. the tip (C
L)
-Spanwise flow, causes some slight compression due the the fuselage resisting this flow, which increases the local density (p)
1+2= inner section producing more lift that the tip, and High to Low = inwards spanwise flow...
Please let me know if this is
but I havn't been caught out using this reasoning in exams
still not sure about the tip stall..
