@Keith:
Nice try but no, I'm with Owain. If you are familiar with non-dimensional representation of turbojet engine performance, then it will be apparent that gross thrust and net thrust at a given altitude are defined by N1/root theta and Mach number. Mach number at a given altitude and IAS does not change with temperature.
Last edited by Gysbreght; 4th Nov 2014 at 17:09.