Hello there,
Thank you all for your feedback !
Max climb thrust is limited by time (manufacturer reccomendations, allthough usually not a factor being a reson why we have climb thrust) speed (n1) and temp (EGT). Having said that there is no such thing as max climb thrust as climb thrust is just a reduction in thrust after a safe altitude is achieved to save money.
Thought as much. I guess what I am more interested in finding is then Max Continuous Thrust. I found figures that suggest that MCT is approx 93% of the max TO thrust (CFM56-3B-2, GE90-76B), and apparently this kind of data is easier to find on the Internet (EASA has some figures). I will look that up. Thanks !
Something I forgot to mention in the initial post: this is for use in an professional ATC simulator. We are trying to get the A/C performance right, and this obviously cannot be achieved until we reproduce reduced-thrust takeoff behaviour in a not too shabby way :-)
In order to do that, one of the important points is to figure out the limiting factor in thrust reduction calculations. In other words, if for example today's A319 can fly a FLEX 49°C but not 50°C, is it usually because of runway length (ASDR > ASDA, my guess) or something else ?
I understand that a required climb gradient (obstacle clearance) could be a restriction here, but I am after the most common limitation really.
Again, thanks for your input. I will edit the original post to reflect the status of each question.
Cheers,
LeCoyote