just to add that without a derate or a flat rate
that thrust is [if i remember right] is about proportional to about N1^3.5
so if thrust or[ drag] decreases with altitude as thrust at any altitude =T[msl]*sqrt [pi]
at any temperature T [msl]* sqrt[
theta]
pi = the pressure ratio
theta =temp. ratio
and it can be seen that the required N1 would be mathematically increased if necessary to counter drag until either a limiting rpm [ if N1 vs EPR limited] or a limiting temp. is achieved for non-accelerated flight
example: T[msl]*sqrt [sigma] ~N1^3.5...
...but for the purpose of meeting performance, N1 would increase to maintain the thrust required to meet performance [although Drag would decrease too] but for acceleration you need thrust GREATER than drag, for performance it's referred to a 'thrust required'
so you are correct
PA