I was recently comparing two aircraft, and, although I feel stupid asking this question, I wondered why one had a maximum speed of M2.2 compared to M0.94, when both have similar weight, both are supersonic capable and both have similar thrust.
Compare for example the Hawker Hunter F.6 which has:
- Empty weight 6,406kg
- Max speed M0.94 (>M1.0 In a dive)
- Engine thrust 10,145lbf
- Climbrate 17,200ft/min
And the Mirage F.1:
- Empty weight 7,050kg
- Max speed M2.2
- Engine thrust 13,700lbf (WET)
- Climbrate 16,400ft/min
As you can see, both have similar rates of climb, similar empty weights, and both are aerodynamically supersonic capable. Only major difference being the the F.1 has ~35% more thrust- yet, with this extra thrust and weight, it is able to go over twice as fast? How does this work?
As I write this the only thing I can think is that wave drag plays a part, and the afterburner is required to give it that extra boost to break through the transonic barrier?
If the above is the case, then does this mean that all aircraft that can supercruise require the use of afterburner to get there, but can then hold it in mil power? And, if so, could this mean theoretically you could use a rocket booster of some form to push the Hunter F.6 through the transonic region and hold a supersonic speed, or, is there a minimum thrust to weight ratio in mil power required to achieve supercruise, or do more special aerodynamics need to be involved to keep wave drag down to make it possible?
