The equation you provided represents the maximum attainable load factor (n) for an aircraft. The load factor is the ratio of the lift force (L) acting on the aircraft to its weight (W). The maximum attainable load factor occurs when the aircraft reaches its maximum lift coefficient (CLmax) and the maximum dynamic pressure, which happens at the aircraft’s critical or stalling angle of attack.
n(max attainable) = 0.5 * ρ * V^2 * S * CLmax / W
Where:
- n(max attainable) is the maximum attainable load factor (dimensionless).
- ρ is the air density (in kg/m³ or slugs/ft³) at the current altitude.
- V is the true airspeed of the aircraft (in m/s or ft/s).
- S is the wing reference area (or planform area) of the aircraft (in square meters or square feet).
- CLmax is the maximum lift coefficient that the aircraft can achieve at its critical angle of attack (dimensionless).
- W is the weight of the aircraft (in newtons or pounds-force).