This means that a safety margin must be used on the main wing area so that its maximum lift coefficient and wing loading are never attained in practice.
32.
Where C _ L is the lift coefficient, " A " is the aspect ratio, and \ epsilon is the aircraft's efficiency factor.
33.
To achieve this stability, the change in canard lift coefficient with angle of attack ( lift coefficient slope ) should be less than that for the main plane.
34.
To achieve this stability, the change in canard lift coefficient with angle of attack ( lift coefficient slope ) should be less than that for the main plane.
35.
The lift coefficient with the wing at this setting was 3.9 ( double that of conventional and contemporary aircraft ), giving a stalling speed of 57 knots.
36.
Experiments have shown that it is not unreasonable to achieve a drag ratio ( \ gamma ) of about 0.01 at a lift coefficient of 0.6.
37.
Instead, the fuselage acts as a very large wing fence and, since wings are generally larger at the root, this raises the maximum lift coefficient allowing a smaller wing.
38.
The sections used were highly cambered in the leading edge with virtually no camber aft of mid chord, producing a section with reduced twisting and pitching moments and high lift coefficients.
39.
In aerodynamics, it is usual to use the top-view projected area of the wing, instead of its frontal area, as a reference surface to define the lift coefficient.
40.
When the wing is stalled and the angle of attack is greater than the stalling angle any increase in angle of attack causes a decrease in lift coefficient that causes the wing to descend.
