# How to compute the mass flow rate for a turboprop at cruise given the static sea level value?

I am trying to obtain the mass flow rate of the Allison T56-A-15 used on the C130H at cruising altitude (so as to solve the Joule-Brayton cycle at cruising altitude). I know from "Turboshaft, Turboprop and Propfan: database Handbook" that the mass flow rate is 14.7 kg/s at static sea level (not sure about the meaning of this). In order to compute the mass flow rate at cruising altitude, what should I do? I've tried writing $$\dot{m} = \rho A_{in} v_{TAS}$$ but in this way I obtain a value of mass flow rate that I consider excessive. Any suggestions?

• Hi and welcome to the site. I have changed the title to match the problem you're solving. Please check the edit and see if other improvements can be made.
– user14897
May 13 at 13:42
• Mass flow is determined by the thrust. May 17 at 22:08