Aircraft Engine Thrust Calculations


Home	Research	For Teachers	HISTORY Level 1 Level 2 Level 3	PRINCIPLES Level 1 Level 2 Level 3	CAREER Level 1 Level 2 Level 3
Gallery	Hot Links	What's New!
Web Administration and Tools

Aircraft Engine Thrust Calculations

In this section, we deal with one of the forces acting on an aircraft, namely, the thrust produced by the aircraft's engine. In the first part of this section we will look at propellers and their efficiency. In the second part of this section, we will provide the formula for the thrust of a jet engine.

Total Propeller Efficiency

Propellers are used to drive many lightweight aircraft and were the principal means of propulsion for military aircraft until the advent of the jet engine. As such, it is important to know how propellers work and how efficient they are. The propeller efficiency can never reach the ideal efficiency of 100 %. This is because in the development of the propeller efficiency several concepts are ignored,

1. The friction drag of the blades.
2. The kinetic energy of the rotation of the slipstream.
3. The fact that the thrust is not uniformly distributed over the blades.

The maximun propeller efficiency is about 90 %. This is due to the combined effects of drag from the nacelle and wings upon the propeller. This combined effect drops propeller efficiency to about 87 %. From there the thrust horsepower provided by the propeller is

where:
= thrust (lb)
= velocity (ft/s)
= engine brake horsepower
550 = conversion factor from ft-lbs to horsepower
= propeller efficiency

Thrust Equation For Turbojet-Type Engines

The thrust equation for a turbojet can be derived from the general form of Newton's second law (i.e., force equals the time rate of change of momentum),

The figure below shows the inlet and exhaust flows of the turbojet. The negative thrust due to bringing the freestream air almost to rest just ahead of the engine is called momentum drag or ram drag. The resulting thrust is given by following equation,

Schematic of a turbojet engine.

where: = is weight flow rate of the air passing through the engine.
= jet stream velocity
= static pressure across propelling nozzle
= atmospheric pressure
= propelling nozzle area
= aircraft speed

The information in this section has been extracted from several sources. Those sources have been contacted and permission to use their material on our site is pending. However, the format in which this material has been presented is copyrighted by the ALLSTAR network.

Funded in part by

Updated: February 23, 1999