Required thrust for given rate of climb Calculator

The required thrust for a given rate of climb refers to the amount of engine power necessary to maintain a specific vertical speed during ascent. It represents the force generated by the aircraft’s engines to overcome drag and gravitational forces while ascending at a desired rate. This parameter is crucial for pilots and aircraft operators to ensure that the aircraft can achieve and maintain the desired climb profile during takeoff, climbout, and en-route phases of flight.

where:

• T_req​ represents thrust, measured in Newtons (N),
• $D$ is the total drag on the aircraft, also measured in Newtons (N),
• $W$ is the weight of the aircraft, measured in Newtons (N),
• $\text{ROC}$ is the rate of climb, typically measured in meters per second (m/s),
• $V$ is the velocity of the aircraft, usually measured in meters per second (m/s).