Currently, AJE assumes that the compressor entry mach is always 0.5, which results in an overestimate of thrust growth with speed. Instead, calculate turbine area when TTR is calculated and assume chocked at all flight conditions (might not be true at low throttle settings).
This will result in a considerable reduction in supersonic thrust - make sure it's not unmanageable.
Currently, AJE assumes that the compressor entry mach is always 0.5, which results in an overestimate of thrust growth with speed. Instead, calculate turbine area when TTR is calculated and assume chocked at all flight conditions (might not be true at low throttle settings).
This will result in a considerable reduction in supersonic thrust - make sure it's not unmanageable.