Why the dynamic pressure is not mentioned in the explanation of lift by Bernoulli's principle? Usual "explanation" of lift using Bernoulli principle

This theory is:


Air over the wing is accelerated, its dynamic pressure increases with velocity.
The static pressure over the wing decreases (due to Bernoulli principle, see below).
The opposite occurs below the wing, static pressure increases.
This results in an imbalance in static pressure between sides, and explains lift origin.


Source


Bernoulli's principle

Bernoulli's principle explains "an increase in the speed of a fluid occurs simultaneously with a decrease in pressure or a decrease in the fluid's potential energy": 

$$p + \frac{1}{2}\rho V^2 + \rho gh = k$$ 

where $k$ is a constant. In the case of a wing, $\rho gh$ is so small it can be omitted, the principle can be stated:

$$p_0 = p + \frac{1}{2}\rho V^2$$

where $p_0$ is a constant known as total pressure, the first term is the static pressure, and the second one the dynamic pressure.

The explanation of lift ignores the imbalance of dynamic pressure

The previous theory ignores a similar, but opposite, imbalance of the dynamic pressure (as the total pressure is constant, the arithmetic sum of the two imbalances is also constant):

  

Why is the force created by static pressure put ahead in the explanation of lift, and the force created by dynamic pressure is not mentioned? If this force is ignored because not significant, why and how much is this force smaller?
In short, "dynamic pressure is not pressure at all" (A Princeton paper on dynamic pressure and Bernoulli's theorem).  "Dynamic pressure" is a term that designates the decrease in pressure, as a consequence of the fluid's / medium's flow velocity.

I recommend that you also examine what NASA has to say:


  Integrating this differential equation:
  
  ps + .5 * r * u^2 = constant = pt
  
  This equation looks exactly like the incompressible form of Bernoulli's equation. Each term in this equation has the dimensions of a pressure (force/area); ps is the static pressure, the constant pt is called the total pressure, and
  
  .5 * r * u^2
  
  is called the dynamic pressure because it is a pressure term
  associated with the velocity u of the flow. Dynamic pressure is often
  assigned the letter q in aerodynamics:
  
  q = .5 * r * u^2