Even an asymmetrical profile does nothing without AOA. At zero AoA its lifting force is downward.... The upper surface has negative AoA due its fatter presentation vice lower, flatter plate.
It is a trick, parlayed into fame by the Swiss plumber.....
See, by the time the flow separates evenly, the aft portion of the flat plate on the bottom has gone Newton.....
Absolutely, 100 percent, purely wrong. Sorry to be blunt, but this is completely untrue. A typical cambered airfoil does produce considerable lift at zero angle of attack.
Here is a
wikipedia article about angle of attack It includes a graph of coefficient of lift for a typical airfoil. You will see that the coefficient of lift at zero AoA is non-zero and positive.
If you're not inclined to believe Wikipedia, here's a
page from NASA on the wright flyer, which includes another graph of lift coefficient vs AoA. It also shows non-zero, positive coefficient of lift at zero AoA. Additionally it contains a table of lift force, and a graph of same. Both show lift force at zero AoA to be non-zero and positive.
Here's
another page showing a a graph of, among other things, the lift coefficient data for the airfoil on a Cessna 172. Coefficient of lift at zero AoA??? non-zero and positive.
Here's a
page from the website of the US centennial of flight.
Care to make any bets as to what's on that page?
If you guessed that it contains a graph of coefficient of lift vs AoA, showing Coefficient of lift to be non-zero and positive at zero AoA, you'd be correct.
Obviously, if your understanding of the facts is this flawed, any conclusions you have drawn from the is inevitably equally flawed.