The drag coefficient can be calculated using the following formula:
$$C_D = \frac{D}{\frac{1}{2}\rho v^2 A}$$
where:
- $C_D$ is the drag coefficient
- $D$ is the drag force acting on the plane
- $\rho$ is the density of the air
- $v$ is the velocity of the plane
- $A$ is the reference area
The reference area is typically the wing area of the plane.
The drag coefficient of a plane is an important parameter in aircraft design, as it affects the plane's performance, fuel consumption, and range. A lower drag coefficient means less drag and therefore improved performance.
