Question

The value of ‘n’ in fuel flow formula C=C2\(\theta^{\frac{1}{2}}\)M^n is 0.6 for turbojet.

(a) True

(b) False

This question was addressed to me in an international level competition.

I want to ask this question from Cruising Performance topic in portion Cruising Performance of Aircraft Performance

Answer 1

Right choice is (b) False

To explain I would say: The correct formula for fuel flow is C=C2\(\theta^{\frac{1}{2}}\)M^n where θ is the temperature, M is mach number and n varies from 0.2-0.6 for turbojet to turbofan. It depends on the bypass ratio of the combustion chamber.