twochai
Your power to weight ratio theory seems logical to me. I am not an aerodynamicist or aeronuatical engineer but have some limited experience in mechnical engineering.
Presumably the climb performance will be affected by how quickly the wing reaches sufficient airspeed to generate the lift required to get the aircraft mass airborne. Therefore the acceleration from start of roll to lift off speed is the important factor and this is where the power/weight ratio is most important?
In hot/high conditions, the air being thinner, engine performance (as with car engines) becomes compromised therefore slowing the acceleration and extending the point where lift off speed is attained (take off distance required).
Am I on the right track?
With regard to the Trident, the BEA meddling with the original specification and the use of the RR Spey was the cause of the aircrafts 'gripper' reputation?