Abstract: A fuel flow measuring system for measuring the flow rate of the fuel in an aircraft and including a turbine flow transmitter which is inserted in the fuel line of the aircraft and produces an output frequency representing a functional relationship to the volume of fuel passing through the flow transmitter, the functional relationship being referred to as the K factor. A control circuit receives the output frequency and converts it into a DC valve representing the flow rate of the fuel. The flow rate is then displayed on an indicator such as a flow meter. A resistor is located in the flow transmitter and is electrically coupled to the control circuit. The resistor is set at a value to compensate for variation in the functional relationship whereas a temperature sensor, also inserted into the transmitter and electrically coupled to the control circuit, serves as a temperature compensator.