TFDi_MD-11_QA/xkhofmann-tfdidesign-md11-config-tweaks
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Engine tuning

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This commit is contained in:
Kilian Hofmann
2025-02-11 14:22:39 +01:00
parent 9ab1d18989
commit 5b98c62dbb
3 changed files with 54 additions and 200 deletions
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PackageSources/SimObjects/Airplanes/TFDi_Design_MD-11F_GE/engines.cfg
+33 -16
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@@ -29,25 +29,32 @@ DisablePropellerControls =1
DisableAutopilotControls=1
[TURBINEENGINEDATA]
fuel_flow_gain=1
//KH From 1, as per SDK warning
fuel_flow_gain=0
low_idle_n1=24.2
low_idle_n2=62.9
inlet_area=9.92
rated_N2_rpm=11055
static_thrust=61960
//KH From 61960 (ideal) as per EASA TCDS for CF6-80C2D1F 5min limit
static_thrust=60690
reverser_available=1
reverser_mach_controlled=0
afterburner_available=0
afterburner_throttle_threshold=0
ThrustSpecificFuelConsumption=0.362
//KH From .362, WikiP lists .3 to .344
ThrustSpecificFuelConsumption=0.344
use_commanded_Ne_Table=1
use_corrected_N2_from_FF_table=1
use_n2_to_n1_table=1
use_old_fuelflow_simvar=1
n2_to_n1_table=0:0:0.85,0:0:0,10:1.1:1,20:2.7:2.4,30:5.7:4.7,40:11.1:9.78,50:16.35:14.9,64.5:25.34:25.39,70:38:37.16,80:59.2:58.56,90:80.4:79.96,99.6:110.75:110.5,105:112:112
mach_0_corrected_commanded_ne_table=0:1:5.42,0:64:64.5,0.143:69.214:69.857,0.286:74.428:75.214,0.429:79.642:80.571,0.572:84.856:85.928,0.715:90.07:91.285,0.858:95.284:96.642,1:100.5:102
mach_hi_corrected_commanded_ne_table=0.88:1:5.42,0:66:67.5,0.143:71.143:72.571,0.286:76.286:77.642,0.429:81.429:82.713,0.572:86.572:87.784,0.715:91.715:92.855,0.858:96.858:97.926,1:102:103
corrected_n2_from_ff_table=0:17,0.0099:63.7,0.01:70,0.017:77.6,0.021:80,0.033:84.77,0.048:88.88,0.083:93,0.088:99.3,0.09:106.5
//KH Compared the ini A300 to the original in Excel. Constructed based on the shape. Increased its max values to those in the TCDS
n2_to_n1_table=0:0:0.85,0:0:0,10:1:1,20:2:2,30:4:4,40:9:9,50:14:14,64.5:25.34:25.34,70:29:29,80:41:41,90:68:68,100:102:102,112.5:117.5:117.5
//KH Adjusted to being linear but with >100 as max
mach_0_corrected_commanded_ne_table=0:1:5.42,0:64:64.5,0.143:70.6495:71.2925,0.286:77.299:78.085,0.429:83.9485:84.8775,0.572:90.598:91.67,0.715:97.2475:98.4625,0.858:103.897:105.255,1:110.5:112
//KH Adjusted to being linear but with >100 as max
mach_hi_corrected_commanded_ne_table=0.88:1:5.42,0:66:67.5,0.143:73.15:74.5785,0.286:80.3:81.657,0.429:87.45:88.7355,0.572:94.6:95.814,0.715:101.75:102.8925,0.858:108.9:109.971,1:116:117
//KH Compared the ini A300 to the original in Excel. Constructed based on the shape
corrected_n2_from_ff_table=0:0,0.02:60,0.03:70,0.04:75.7,0.055:81.4,0.07:87.1,0.09:92.8,0.11:98.5,0.13:104.2,0.15:112.5
n1_and_mach_on_thrust_table=0:0:0.25:0.39:0.49:0.5:0.67:0.74:0.8:0.82:0.85,0:0:0:0:0:0:0:0:0:0:0,20:0.0554:0.0598:0.0598:0.0598:0.0205:0.0282:0.0404:0.0411:0.0224:0.0297,25:0.0748:0.0704:0.0704:0.1304:0.1291:0.1235:0.1278:0.1262:0.1291:0.0393,30:0.0865:0.0821:0.0821:0.0335:0.0547:0.0847:0.0847:0.1039:0.1039:0.1039,35:0.0964:0.0963:0.0963:0.0425:0.0601:0.0901:0.0901:0.1053:0.1053:0.1053,40:0.1312:0.1134:0.1134:0.1007:0.092:0.102:0.102:0.1156:0.1161:0.1176,45:0.163:0.1278:0.1278:0.13:0.3795:0.4095:0.4095:0.4235:0.4235:0.4235,50:0.1816:0.1448:0.1448:0.1518:0.3853:0.4153:0.4153:0.4389:0.4389:0.4389,55:0.2388:0.1711:0.1632:0.1715:0.3906:0.4206:0.4206:0.442:0.442:0.442,60:0.2726:0.2079:0.1902:0.2076:0.3943:0.4243:0.4243:0.446:0.446:0.446,65:0.3294:0.2532:0.2336:0.2367:0.4002:0.4302:0.4302:0.4542:0.4542:0.4542,70:0.3807:0.3116:0.2786:0.2768:0.409:0.439:0.439:0.4642:0.4642:0.4642,75:0.4477:0.3938:0.3318:0.3282:0.4274:0.4574:0.4574:0.4705:0.4703:0.4706,80:0.5395:0.4915:0.4124:0.4138:0.4321:0.4621:0.4621:0.484:0.4813:0.4805,85:0.6524:0.6349:0.5626:0.5072:0.5044:0.5355:0.5309:0.5785:0.5275:0.5356,90:0.7545:0.7735:0.6998:0.61:0.61:0.6173:0.6574:0.6638:0.6044:0.6297,95:0.8364:0.8395:0.7080:0.6900:0.7010:0.7296:0.8207:0.8673:0.7222:0.7682,103.5:0.9779:0.9811:0.7157:0.7212:0.744:0.7453:0.8651:0.9026:0.9209:0.9312,110:0.9853:1.0945:0.7775:0.83:0.85:0.8257:0.8749:0.9122:0.9322:0.9317,120:0.857:0.9826:0.7877:0.84:0.88:0.8339:0.8818:0.9131:0.9473:0.9404
corrected_airflow_table=0:0:0.9,0:0:0,20:4.29:14.08,85:4.62:24,90:5.75:25,95:7.23:27,100:8.36:28,105:9.29:29,120:10.94:30
JET_density_on_FF_table=0.000462:28.74,0.000587:32.93,0.000738:35.02,0.000891:29.46,0.001066:31.02,0.001267:32.56,0.001496:34.54,0.0017565:35.11,0.002048:30.8,0.002377:22.55
@@ -64,10 +71,14 @@ oil_press_tc=0.8
oil_press_tuning_constant=1
itt_peak_temperature=2141
itt_tc=2
//KH No scaling
itt_tuning_constant=1
egt_peak_temperature=1600
egt_tc=0.1
egt_tuning_constant=0.1
//KH 750C Start limit as per EASA TCDS for CF6-80C2D1F
egt_peak_temperature=1841
//KH Taken from the A300, made sense
egt_tc=2
//KH No scaling
egt_tuning_constant=1
fuel_press_max=2376
fuel_press_tc=2
fuel_press_tuning_constant=1
@@ -86,11 +97,14 @@ min_n2_for_apu_bleed_air_cutoff=50
n1_normal_tc=0.5
n1_start_max_rate=1
n1_start_combustion_max_rate=2
idle_fuel_flow=600
//KH From 600, used videos from YT as rough basis
idle_fuel_flow=1400
idle_high_fuel_flow=40
min_n2_for_fuel_flow=17
high_n1=110
high_n2=105
//KH From 110 as per EASA TCDS for CF6-80C2D1F
high_n1=117.5
//KH From 105 as per EASA TCDS for CF6-80C2D1F
high_n2=112.5
high_fuel_flow=9800
mach_influence_on_n1=10
fuel_flow_max=10000
@@ -100,9 +114,12 @@ fuel_flow_controller_d=0.1
fuel_flow_controller_iboundary=10
fuel_flow_controller_dboundary=100
max_torque_protection=0
max_n1_protection=110
max_n2_protection=100
max_egt_protection=2000
//KH Disabled
max_n1_protection=0
//KH Disabled
max_n2_protection=0
//KH Disabled
max_egt_protection=0
fuel_flow_max_itt_factor=2
fuel_flow_min_itt_factor=0.9
n1_cooling_factor=0.01