Mach / Thrust Question
Could anyone point me to a reference/explanation for the following statement:
At a fixed pressure altitude, a set amount of thrust will produce a specific Mach number (i.e. the properties of Mach account for any variance in temperature).
Further to this, I'd appreciate any pointers as to the variables that keep this from being the case with a propeller aircraft (horsepower vs thrust, prop efficency variable with speed, etc).
Appreciate any thoughts that you can provide (or more importantly, a good reference...)