Thrust Coefficient For a LM C-130 Hercules Calculator

The thrust coefficient of an aircraft is a dimensionless parameter that relates the thrust produced by the aircraft’s propulsion system to the dynamic pressure of the incoming air.

For the C-130 Hercules, additional considerations may include payload capacity, range, and endurance. While the specific design and performance characteristics of the C-130 Hercules may not be captured by a single thrust coefficient, these traditional aerodynamic parameters provide a basis for evaluating its flight performance.

The thrust coefficient is defined as the ratio of the thrust force produced by the propulsion system to the dynamic pressure of the incoming air. Mathematically, it is expressed as:

where,

where:

• C_T​ is the thrust coefficient,
• $T$ is the thrust force,
• $\rho$ is the air density,
• $V$ is the airspeed,
• $A$ is the reference area.