Video proof of zone theory demonstrating its validity is presented in the following set of videos. The theory can be seen working in the real conditions of moving airfoil, as in actual flight. These videos are not of wind tunnel experiments and distinctively show actual pressure enhancements/reductions in the air mass in which the airfoil moves. The videos prove the theory beyond any doubts. The point to note is that NO wind tunnel experiment or CFD simulation can prove or demonstrate this way of how an airfoil actually functions to generate lift. Its purely a Tekemon distinction.
The function of the airfoil is to create the pressure difference on its top which generates lift. The purpose of the video proof is to clearly show these invisible pressure zones over the wing.
Postulate-2
An airfoil wing moving in air creates two distinct regions of different pressures, over its top surface. These are called the forward Subduction-Zone and the rear Induction-Zone. The Subduction-Zone is a region immediately around the leading edge, and extends backwards up to the zero-slope line on the airfoil. The pressure in the Subduction-Zone is above atmospheric pressure. The Induction-Zone is a region of less than normal atmospheric pressure between the zero-slope line and the trailing edge.
These pressure zones are demonstrated in videos 1 & 2 below. The styrofoam detector initially rises up over the wing due to the high pressure subduction zone, and then gets sucked into the induction zone. Notice how the leading edge of the detector follows the curvature of the wing top, under influence of the vacuum generated by the inductor.
VIDEO-1 & 2 (Proof of Postulate-2 above)
Postulate-3
The airfoil inductor generates the vacuum first (due to finite-time required by the surrounding air mass to fill the void created by the moving airfoil) and then as a result of this vacuum air is inducted (sucked) over the wing top, from the subduction zone into the induction zone, in the direction from the leading edge towards the trailing edge. This simulated transient backwards flow called Ftr ceases immediately at the trailing edge, as evident by abrupt braking of a balloon after airfoil has passed onwards to next one in line, in the two videos below. Ftr is the effect not the cause, of the vacuum generated by the inductor. Hence this flow does not generate lift, as wrongly attributed to the principle of Bernoulli or Coanda Effect.
VIDEO-3 & 4 (Proof of Postulate-3 above)
VIDEOS-5,6,7 (Video Proof of Zone Strength at Various Wing Speeds)
Note: Other video proof are under development and will be posted as and when available.