LIFT review

1.) blade angle is the angular difference between the angle of the blade and plane of rotation.
2.) feathering a blade meas changing its pitch angle around the feathering axis (done so with collective or cyclic).
3.) when an airflow is deflected by an airfoil, the force is acting more or less at right angles to the relative airflow(relative wind) and drag acts parallel to the relative flow.
4.) the two components of total lift reaction are lift, and drag, parallel to the relative airflow.
5.) when an airflow is made to speed up, the pressure with in the flow decreases provided the flow remains constant (Bernoulli's principle.)
6.) when a symmetrical airfoil is placed at a zero degree angle of attack to an airflow, pressures are the same above and below the airfoil.
7.) the lift coefficient of an airfoil is determined by its area and shape.
8.) the peak of the Cl curve represents (coefficient of lift max./coefficient of lift min.), the associated angle of attack is called the pitch angle.
9.) the C/P is the point on the chord line through which all weights are said to act.
10.) the C/P of a symmetrical airfoil remains steady with changes in angle of attack.
11.) the point on the chord line about which no change in pitch moments is felt with changes in angle of attack is called the aerodynamic center.