Sorry for huge comment....
Corrected thrust, speed, control surfaces, aerodynamics, and a lot more. It has to be flown in legacy. For some reason in "Modern" a hard speed limit of Mach 0.95 is in place.
engines.cfg
[VERSION]
major = 1
minor = 0
[GENERALENGINEDATA]
engine_type = 1 ; 0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
fuel_flow_scalar = 1 ; Fuel flow scalar
min_throttle_limit = -0.25 ; Minimum percent throttle. Generally negative for turbine reverser
master_ignition_switch = 0
starter_type = 0 ; 0=Electric, 1=Manual, 2=Bleed Air
max_contrail_temperature = -39.724
Engine.0 = -13, -2.0, 3.5
ThrustAnglesPitchHeading.0 = 0, 0
Engine.1 = -13, 2.0, 3.5
ThrustAnglesPitchHeading.1 = 0, 0
[TURBINEENGINEDATA]
fuel_flow_gain = 0.005 ; Gain on fuel flow
inlet_area = 3 ; Square Feet, engine nacelle inlet area
rated_N2_rpm = 22000 ; RPM, second stage compressor rated value
static_thrust = 35000 ; Lbs, max rated static thrust at Sea Level
reverser_available = 1
reverser_mach_controlled = 0
afterburner_available = 0
afterburner_throttle_threshold = 0.7
ThrustSpecificFuelConsumption = 0.5
AfterBurnThrustSpecificFuelConsumption = 0
mach_0_corrected_commanded_ne_table = 0.000000:1.000000:22.570000,0.000000:55.000000:82.500000,0.420000:78.800003:95.400002,0.510000:82.500000:98.500000,0.610000:87.400002:101.099998,0.700000:92.000000:103.099998,0.790000:96.199997:105.699997,0.930000:103.099998:108.059998,1.000000:107.000000:108.059998
mach_hi_corrected_commanded_ne_table = 0.900000:1.000000:22.570000,0.000000:62.000000:82.500000,0.420000:77.000000:95.400002,0.510000:80.199997:98.500000,0.610000:84.800003:101.099998,0.700000:89.099998:103.099998,0.790000:92.199997:105.699997,0.930000:96.000000:108.059998,1.000000:98.199997:108.059998
corrected_n2_from_ff_table = 0.000000:0.000000, 0.002940:10.000000, 0.011800:30.000000, 0.020660:40.000000, 0.033970:50.000000, 0.053170:60.000000, 0.133910:80.000000, 0.257710:90.000000, 0.540000:100.000000, 0.686860:105.000000
n1_and_mach_on_thrust_table = 0.000000:0.000000:0.900000,0.000000:0.000000:0.000000,20.000000:0.025400:0.114000,25.000000:0.050800:0.222000,30.000000:0.079800:0.350000,35.000000:0.112500:0.451000,40.000000:0.152400:0.545000,45.000000:0.199500:0.640000,50.000000:0.254000:0.754000,55.000000:0.360000:0.869000,60.000000:0.480000:0.953000,65.000000:0.572000:1.040000,70.000000:0.653000:1.126000,75.000000:0.727000:1.210000,80.000000:0.788000:1.295000,85.000000:0.875000:1.378000,90.000000:0.985000:1.478000,95.000000:1.061000:1.578000,100.000000:1.153000:1.668000,105.000000:1.237000:1.778000,110.000000:1.338000:1.845000
n2_to_n1_table = 0.000000:0.000000:0.900000,0.000000:0.000000:0.000000,10.000000:2.000000:9.200000,20.000000:7.000000:14.600000,30.000000:10.200000:20.000000,40.000000:15.100000:24.700001,50.000000:20.100000:32.000000,60.000000:28.000000:41.799999,70.000000:38.000000:53.200001,80.000000:52.000000:67.500000,90.000000:70.000000:80.800003,100.000000:89.400002:100.800003,110.000000:112.000000:120.000000
corrected_airflow_table = 0.000000:0.000000:0.100000:0.200000:0.300000:0.400000:0.500000:0.600000:0.700000:0.800000:0.900000,0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000,20.000000:3.669446:4.387084:5.730836:6.842790:7.698139:8.235298:8.834042:9.770649:10.667910:12.044166,25.000000:5.184269:5.742812:7.098539:8.296883:8.981162:9.472132:10.070021:10.927080:11.725121:12.961100,30.000000:6.680274:7.138741:8.254971:9.591025:10.209442:10.787659:11.406075:12.123713:12.881552:13.958436,35.000000:8.195951:8.534670:9.451604:10.548161:11.246125:12.003964:12.682256:13.340019:13.998637:14.975446,40.000000:9.691101:9.930599:10.628564:11.665246:12.442759:13.280145:13.978109:14.496450:15.095195:15.932581,45.000000:11.246125:11.326528:11.984291:12.821677:13.639391:14.556325:15.254290:15.693084:16.251627:16.929918,50.000000:12.722457:12.761804:13.340019:14.078185:14.875370:15.832505:16.550999:16.849514:17.367857:17.887053,55.000000:14.217607:14.217607:14.735949:15.334692:16.172079:17.089012:17.827179:18.065821:18.465269:18.803988,60.000000:15.733285:15.752957:16.311501:16.729767:17.527807:18.324991:19.262453:19.222252:19.621700:19.801323,65.000000:17.129213:17.248962:17.767303:18.185570:18.823660:19.601171:20.080168:20.379539:20.737930:20.718258,70.000000:18.684238:18.803988:19.282127:19.641373:20.159714:20.818333:21.216925:21.535971:21.834488:21.675392,75.000000:20.239262:20.399212:20.737930:21.157051:21.555643:22.073984:22.512779:22.752277:22.692402:22.572653,80.000000:21.914890:22.034639:22.353683:22.652201:22.991774:23.510115:23.829161:23.948910:23.808632:23.748758,85.000000:23.808632:23.829161:24.108004:24.327829:24.546799:24.825642:25.165215:25.105341:25.005264:24.945391,90.000000:25.882853:25.909369:25.935884:25.963255:25.989771:26.016287:26.042803:26.070175:26.096689:26.123205,95.000000:27.478079:27.504595:27.531111:27.558481:27.584997:27.611513:27.638029:27.665400:27.691916:27.718431,100.000000:28.734585:28.761101:28.787617:28.814133:28.841505:28.868019:28.894535:28.921051:28.948423:28.974939,105.000000:29.691721:29.718237:29.744753:29.771269:29.798639:29.825155:29.851671:29.878187:29.905558:29.932074,110.000000:30.189533:30.216906:30.243422:30.269938:30.296452:30.323824:30.350340:30.376856:30.403372:30.430742
epr_max = 26.8 ; 1.4
epr_tc = 6 ; 14
epr_tuning_constant = 1
oil_temp_cooling_constant = 0.21
oil_temp_heating_constant = 700
oil_temp_tc = 0.03
oil_temp_tuning_constant = 1
oil_press_max = 11376
oil_press_tc = 0.8
oil_press_tuning_constant = 1
itt_peak_temperature = 2400
itt_tc = 2
itt_tuning_constant = 1
egt_peak_temperature = 1285
egt_tc = 2
egt_tuning_constant = 1
fuel_press_max = 5000 ; 2376
fuel_press_tc = 2
fuel_press_tuning_constant = 1
variable_inlet = 0
primary_nozzle_available = 1
primary_nozzle_afterburner_offset = 0.14
primary_nozzle_n1_mach_to_nozzle_pos = 0.000000:0.000000:2.000000,53.000000:0.660000:0.100000,65.000000:0.690000:0.330000,96.000000:0.700000:0.440000
density_on_torque_table = 0.000225:0.100000, 0.000350:0.600000, 0.000400:0.800000, 0.000450:1.000000, 0.002378:1.000000
starter_N1_max_pct = 12 ; Pct, percentage of max rpm that reached using only starter.
starter_N1_rate = 12 ; Rate at which the starter N1 increases.
ignition_auto_type = "0" ; If the Ignition is set to AUTO - specifies how that is handled. 0(default) = Always on, 1 = Ignition follows starter status, 2 = Ignition enabled when Flaps are not neutral, when AntiIce is enabled, or when N1/N2 is below 50%.
min_condition_lever_for_combustion = 0.01 ; % - Minimum position of the Condition lever to obtain a combustion. Default at 0.01.
min_n1_for_combustion = 10 ; % - Minimum N1 required to maintain a combustion
min_n2_for_combustion = 19.4 ; % - Minimum N2 required to maintain a combustion
min_n1_for_starter_cutoff = 200 ; % - Minimum N1 at which the starter is automatically disabled
min_n2_for_starter_cutoff = 50 ; % - Minimum N2 at which the starter is automatically disabled
min_n2_for_apu_bleed_air_cutoff = 200 ; % - Minimum N2 at which the APU Bleed Air is automatically disabled
n2_from_bleed_air_psi_table = 0:0, 4:8, 10:18, 18:25 ; Table which contains the n2 generated depending on the pression from the bleed air from the APU (in psi).
bleed_air_on_n2_tc = 1 ; Time constant which contains the speed at which the bleed air pressure affect the N2 of the turbine.
N1_to_oil_pressure_table = 0:0, 0.21:0.88, 0.9:0.954, 1:1 ; % of max Oil Pressure for % N1.
n1_normal_tc = 0.5 ; Float factor changing N1 acceleration during normal use of the engine
n1_start_max_rate = 1.0 ; Float limiting N1 acceleration during starter use
n1_start_combustion_max_rate = 2.0 ; Float limiting N1 acceleration during startup when cumbustion has started
idle_fuel_flow = 350 ; pound per hour
low_idle_n1 = 20
low_idle_n2 = 60
high_n1 = 100
high_n2 = 100
high_fuel_flow = 3000
min_n2_for_fuel_flow = 22
mach_influence_on_n1 = 10
fuel_flow_max = 6000 ; 3500
fuel_flow_controller_p = 0.5
fuel_flow_controller_i = 0.01
fuel_flow_controller_d = 0.1
fuel_flow_controller_iboundary = 10
fuel_flow_controller_dboundary = 100
max_torque_protection = 0 ; 0 = no protection, value of the torque triggering a protection by automatically limiting the fuelflow
max_n1_protection = 0 ; 104 ; 0 = no protection, value of the n1 triggering a protection by automatically limiting the fuelflow
max_n2_protection = 0 ; 105 ; 0 = no protection, value of the n2 triggering a protection by automatically limiting the fuelflow
max_egt_protection = 0 ; 2000 ; 0 = no protection, value of the egt triggering a protection by automatically limiting the fuelflow
[JET_ENGINE]
thrust_scalar = 1
[DISABLED_CONTROLS]
DisableFuelValveControls = 0 ; Disable fuel valve controls
DisableMixtureControls = 0 ; Disable mixture controls
DisableParkingBrakeControls = 0 ; Disable parking brake controls
DisablePropellerControls = 0 ; Disable propeller controls
Trying to post flight_model.cfg next. Can't add here due to comment size.