The Cg coefficient, or center of gravity coefficient, is a dimensionless number that represents the distribution of an aircraft’s weight relative to its lift and wing span. It is a critical parameter in aircraft design and performance, as it affects the stability and control of the aircraft. The Cg coefficient helps in determining the optimal loading and balance of the aircraft to ensure safe and efficient flight operations.
The formula to calculate the Cg coefficient (Cg) is:
\[ Cg = \left( \frac{L \times d}{W \times b} \right) \]
Where:
Let's say the lift force is 5000 N, the distance from the reference point is 2 m, the weight of the aircraft is 10000 N, and the wing span is 10 m. Using the formula:
\[ Cg = \left( \frac{5000 \times 2}{10000 \times 10} \right) \]
We get:
\[ Cg = \left( \frac{10000}{100000} \right) = 0.1 \]
So, the Cg coefficient (\( Cg \)) is 0.1.
