Hope I've posted this in correct forum...
I've just been reading about the F-14, and more specifically its top speed was given in MPH. In a modern airline one cruises at, grab a figure, Mach 0.79, to avoid supersonic airflow over the wings? The engines aren't operating at maximum thrust, but perhaps N1 93%. More power is available, but an increase in speed would exceed MachCrit?
If I'm correct, military supersonic aircraft are immune to supersonic airflow issues over the wing. Is the aircraft top speed simply limited by thrust running out at high speeds??? Presumably the airframe would happily go faster?? Also the IAS at the quoted speeds of 1400 MPH at circa FL600 (ceiling height) would presumably be approaching low speed stall speeds (IAS)?
Also, above the tropopause, mach 1 is about 573 knots. 38.94xsqare root absolute T. Mach 2 would then be 1320 MPH (converted), but the aircraft is described as capable of mach 1 point something, but 1400 is over Mach 2.....
can somebody see where I'm confusing myself? I would be most grateful.