Happy eng, start EGT & new ground
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@ -35,27 +35,24 @@ low_idle_n1=24.2
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low_idle_n2=62.9
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inlet_area=9.92
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rated_N2_rpm=11055
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//KH From 61960 (ideal) as per EASA TCDS for CF6-80C2D1F 5min limit
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static_thrust=60690
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static_thrust=61960
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reverser_available=1
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reverser_mach_controlled=0
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afterburner_available=0
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afterburner_throttle_threshold=0
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//KH From .362, WikiP lists .3 to .344
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ThrustSpecificFuelConsumption=0.344
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//KH Unchanged, 0.304 to .344 according to GE, leaning towards .344 for the 80C2D1F
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ThrustSpecificFuelConsumption=0.362
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use_commanded_Ne_Table=1
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use_corrected_N2_from_FF_table=1
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use_n2_to_n1_table=1
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use_old_fuelflow_simvar=1
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//KH Compared the ini A300 to the original in Excel. Constructed based on the shape. Increased its max values to those in the TCDS
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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
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//KH Adjusted to being linear but with >100 as max
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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
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//KH Adjusted to being linear but with >100 as max
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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
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//KH Compared the ini A300 to the original in Excel. Constructed based on the shape
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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
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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
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//KH START Modified
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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
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mach_0_corrected_commanded_ne_table=0:1:5.42,0:64:64.5,0.143:69.214:69.857,0.286:74.428:75.214,0.429:79.642:80.571,0.572:84.856:85.928,0.715:90.07:91.285,0.858:95.284:96.642,1:102.5:104
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mach_hi_corrected_commanded_ne_table=0.88:1:5.42,0:66:67.5,0.143:71.143:72.571,0.286:76.286:77.642,0.429:81.429:82.713,0.572:86.572:87.784,0.715:91.715:92.855,0.858:96.858:97.926,1:108:109
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corrected_n2_from_ff_table=0:17,0.00991:64.5,0.01992:70,0.02993:75,0.03994:80,0.04996:85,0.05997:90,0.06998:95,0.07999:100,0.09:106.5
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n1_and_mach_on_thrust_table=0:0:0.25:0.39:0.49:0.5:0.67:0.74:0.8:0.82:0.85,0:0:0:0:0:0:0:0:0:0:0,20:0.0304:0.0598:0.0598:0.0598:0.0205:0.0282:0.0404:0.0411:0.0224:0.0297,25:0.0408:0.0704:0.0704:0.1304:0.1291:0.1235:0.1278:0.1262:0.1291:0.0393,30:0.0635:0.0821:0.0821:0.0335:0.0547:0.0847:0.0847:0.1039:0.1039:0.1039,35:0.0924:0.0963:0.0963:0.0425:0.0601:0.0901:0.0901:0.1053:0.1053:0.1053,40:0.1212:0.1134:0.1134:0.1007:0.092:0.102:0.102:0.1156:0.1161:0.1176,45:0.147:0.1278:0.1278:0.13:0.3795:0.4095:0.4095:0.4235:0.4235:0.4235,50:0.1816:0.1448:0.1448:0.1518:0.3853:0.4153:0.4153:0.4389:0.4389:0.4389,55:0.2388:0.1711:0.1632:0.1715:0.3906:0.4206:0.4206:0.442:0.442:0.442,60:0.2726:0.2079:0.1902:0.2076:0.3943:0.4243:0.4243:0.446:0.446:0.446,65:0.3294:0.2532:0.2336:0.2367:0.4002:0.4302:0.4302:0.4542:0.4542:0.4542,70:0.3807:0.3116:0.2786:0.2768:0.409:0.439:0.439:0.4642:0.4642:0.4642,75:0.4477:0.3938:0.3318:0.3282:0.4274:0.4574:0.4574:0.4705:0.4703:0.4706,80:0.5395:0.4915:0.4124:0.4138:0.4321:0.4621:0.4621:0.484:0.4813:0.4805,85:0.6524:0.6349:0.5626:0.5072:0.5044:0.5355:0.5309:0.5785:0.5275:0.5356,90:0.7545:0.7735:0.6998:0.61:0.61:0.6173:0.6574:0.6638:0.6044:0.6297,95:0.8364:0.8395:0.708:0.69:0.701:0.7296:0.8207:0.8673:0.7222:0.7682,103.5:0.9779:0.9811:0.7157:0.7212:0.744:0.7453:0.8651:0.9026:0.9209:0.9312,110:0.9853:0.9826:0.7775:0.83:0.85:0.8257:0.8749:0.9122:0.9322:0.9317,120:1:0.9945:0.7877:0.84:0.88:0.8339:0.8818:0.9131:0.9473:0.9404
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//KH END Modified
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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
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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
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epr_max=1.8
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@ -69,15 +66,15 @@ oil_temp_factor_from_rpm=0.00:0.80, 250.00:0.80, 500.00:0.80, 2500.00:1.00, 4000
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oil_press_max=13000
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oil_press_tc=0.8
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oil_press_tuning_constant=1
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itt_peak_temperature=2141
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itt_tc=2
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//KH No scaling
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//KH From 2141, 600 above EGT
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itt_peak_temperature=2531
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itt_tc=3
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itt_tuning_constant=1
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//KH 750C Start limit as per EASA TCDS for CF6-80C2D1F
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egt_peak_temperature=1841
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//KH Taken from the A300, made sense
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egt_tc=2
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//KH No scaling
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//KH From 1600, 800C
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egt_peak_temperature=1931
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//KH From 0.1, taken from the A300, made sense
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egt_tc=3
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//KH From 0.1
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egt_tuning_constant=1
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fuel_press_max=2376
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fuel_press_tc=2
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@ -97,14 +94,15 @@ min_n2_for_apu_bleed_air_cutoff=50
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n1_normal_tc=0.5
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n1_start_max_rate=1
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n1_start_combustion_max_rate=2
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//KH From 600, used videos from YT as rough basis
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idle_fuel_flow=1400
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//KH Unchanged, IRL closer to 1200
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idle_fuel_flow=600
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idle_high_fuel_flow=40
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min_n2_for_fuel_flow=17
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//KH From 110 as per EASA TCDS for CF6-80C2D1F
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high_n1=117.5
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//KH From 105 as per EASA TCDS for CF6-80C2D1F
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high_n2=112.5
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//KH Unchanged, IRL 117.5 as per EASA TCDS for CF6-80C2D1F
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high_n1=110
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//KH Unchanged, IRL 112.5 as per EASA TCDS for CF6-80C2D1F
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high_n2=105
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//KH Unchanged, IRL closer to 15500
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high_fuel_flow=9800
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mach_influence_on_n1=10
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fuel_flow_max=10000
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@ -120,12 +118,16 @@ max_n1_protection=0
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max_n2_protection=0
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//KH Disabled
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max_egt_protection=0
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fuel_flow_max_itt_factor=2
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fuel_flow_min_itt_factor=0.9
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//KH From 2
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fuel_flow_max_itt_factor=2.5
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//KH From 0.9
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fuel_flow_min_itt_factor=0.74
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n1_cooling_factor=0.01
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n2_from_bleed_air_psi_table=0.0:0.0, 4.0:8.0, 10.0:18.0, 18.0:25.0
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bleed_air_on_n2_tc=1
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N1_to_oil_pressure_table=0.00:0.00, 0.21:0.71, 0.90:0.99, 1.00:1.00
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//KH New
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itt_maxcorrection=400
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[JET_ENGINE]
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thrust_scalar=1.0
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@ -1,7 +1,8 @@
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//TFDi Designs MD-11F (GE CF6-80C2D1F) vRC1.4_GE_F 29AUG24
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[VERSION]
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major = 3
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//KH Bump major
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major = 4
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minor = 1
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[WEIGHT_AND_BALANCE]
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@ -282,7 +283,15 @@ stall_coef_at_min_weight = 0.71
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ground_crosswind_effect_zero_speed=10
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ground_crosswind_effect_max_speed=150
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ground_high_speed_steeringwheel_static_friction_scalar=1.5
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ground_high_speed_otherwheel_static_friction_scalar=1.2
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ground_high_speed_otherwheel_static_friction_scalar=1.2
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//KH New ground physics
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ground_new_contact_model_gear_flex=0.0035
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ground_new_contact_model_gear_flex_damping=12
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ground_new_contact_model_rolling_stickyness=0.25
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ground_new_contact_model_up_to_speed_lateral=10000
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ground_new_contact_model_up_to_speed_lateral_steering=10000
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ground_new_contact_model_up_to_speed_longitudinal=10000
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enable_high_accuracy_integration=1
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[REFERENCE SPEEDS]
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full_flaps_stall_speed = 115
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71
README.MD
71
README.MD
@ -1,11 +1,66 @@
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# How to export a package
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- If a new blender export was done, run `pnpm model`.
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- Export from MSFS
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# Adjustments
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- Dropped idle thrust so so that aircraft doesn't start rolling when not nearly
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empty
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- Affected by `n1_and_mach_on_thrust_table`
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- Adjusted idle down on 0 mach entries only
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- Smoothed low end
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- Adjusted mach 0 curve to end at 1
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- Adjusted mach 0.25 curve to have a similar end to mach 0
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- Adjusted mach 0.74 curve to have a similar end to the surrounding
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- Spool behaviour after 90 N1
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- Affected by `corrected_n2_from_ff_table`
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- Set idle N2 FF value directly
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- Made linear until original max
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- EGT
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- Affected by `itt_peak_temperature`, `itt_tc`, `egt_peak_temperature`,
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`egt_tc`, `egt_tuning_constant`, `fuel_flow_max_itt_factor`,
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`fuel_flow_min_itt_factor`, `itt_maxcorrection`
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- At ISA, SL, 60C, EGT does not exceed 960C TO
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limit
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- Used online references to achieve idle EGT
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- Used Saudi FCOM for high altitude EGT
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- This may be unachievable due to the non changeable cooling of the game
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- Disabled sim protections
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- Affected by `max_n1_protection`, `max_n2_protection`, `max_egt_protection`
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- All set to zero
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- SDK conformance
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- Affected by `fuel_flow_gain`
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- Set to zero as the SDK indicated one ought to
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# Additions
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- New ground contact model
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# Observations
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The defined N1 and N2 max values are too low. as per EASA TCDS, the CF6-80C2D1F
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has a N1 max of 117.5 and a N2 max of 112.5. I do not know why the lower limits
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were chosen, it may be in our interest to adjust this to the actual limits.
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This may also influence the WASM since FADEC response and thrust limit
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selection may need to be adjusted to allow values higher than currently
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possible.
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The curves that `n1_and_mach_on_thrust_table` look very strange. I do not fully
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understand how these were generated, and more importantly, why they have these
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shapes. Specifically the plateau and the bump at 25 N1 for the higher machs are
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odd. Comparisons with other addons yielded mixed results, however all of those
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curves did not have (or only in regimes unattainable during higher machs) such
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oddities.
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Also to note is the drop in thrust for 120 N1 at mach 0 and mach 0.25. This
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seems backwards to what physics would suggest, with higher RPM generating more
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thrust.
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The curves for `n2_to_n1_table` end in a rather sharp plateau. Without knowing
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how the actual CF6 behaves, this may be closer to reality than a pure
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logarithmic relation of N2 to N1 would suggest.
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`corrected_n2_from_ff_table` is an oddball. If the game is told to not use this
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table, a default logarithmic curve is used instead. The modifications done here
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do not follow this due to the WASM FADEC imposing a non linear spool behaviour
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itself. It is to note however, that the sharp upturn at the end of the original
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lead to a noticeable increase in spool past 90 N1, after first seemingly
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slowing down at 75 to 80 N1.
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# TODO
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Transfer changes into an unsorted copy of the F for Martyn
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Tackle:
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- Temps
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- Ground roll drag
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- EGT, try higher ITT with new tuning params
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- New ground contact MTOW sponginess
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- New ground contact high speed stickyness
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- AND trim issue
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@ -1,4 +1,71 @@
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const inp =
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``;
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const tables = {
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n2_to_n1_table: `0 0 0.85
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0 0 0
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10 1.1 1
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20 2.7 2.4
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30 5.7 4.7
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40 11.1 9.78
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50 16.35 14.9
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64.5 25.34 25.39
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70 38 37.16
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80 59.2 58.56
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90 80.4 79.96
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99.6 110.75 110.5
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105 112 112`,
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mach_0_corrected_commanded_ne_table: `0 1 5.42
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0 64 64.5
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0.143 69.214 69.857
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0.286 74.428 75.214
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0.429 79.642 80.571
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0.572 84.856 85.928
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0.715 90.07 91.285
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0.858 95.284 96.642
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1 102.5 104`,
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mach_hi_corrected_commanded_ne_table: `0.88 1 5.42
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0 66 67.5
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0.143 71.143 72.571
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0.286 76.286 77.642
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0.429 81.429 82.713
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0.572 86.572 87.784
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0.715 91.715 92.855
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0.858 96.858 97.926
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1 108 109`,
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corrected_n2_from_ff_table: `0 17
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0.00991 64.5
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0.01992 70
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0.02993 75
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0.03994 80
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0.04996 85
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0.05997 90
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0.06998 95
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0.07999 100
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0.09 106.5`,
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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
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0 0 0 0 0 0 0 0 0 0 0
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20 0.0304 0.0598 0.0598 0.0598 0.0205 0.0282 0.0404 0.0411 0.0224 0.0297
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25 0.0408 0.0704 0.0704 0.1304 0.1291 0.1235 0.1278 0.1262 0.1291 0.0393
|
||||
30 0.0635 0.0821 0.0821 0.0335 0.0547 0.0847 0.0847 0.1039 0.1039 0.1039
|
||||
35 0.0924 0.0963 0.0963 0.0425 0.0601 0.0901 0.0901 0.1053 0.1053 0.1053
|
||||
40 0.1212 0.1134 0.1134 0.1007 0.092 0.102 0.102 0.1156 0.1161 0.1176
|
||||
45 0.147 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 0.708 0.69 0.701 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 0.9826 0.7775 0.83 0.85 0.8257 0.8749 0.9122 0.9322 0.9317
|
||||
120 1 0.9945 0.7877 0.84 0.88 0.8339 0.8818 0.9131 0.9473 0.9404`,
|
||||
};
|
||||
|
||||
console.log(inp.replaceAll("\t", ":").replaceAll("\n", ","));
|
||||
for (const table_name in tables) {
|
||||
const table = tables[table_name];
|
||||
console.log(
|
||||
`${table_name}=${table.replaceAll("\t", ":").replaceAll("\n", ",")}`
|
||||
);
|
||||
}
|
||||
|
||||
@ -11,6 +11,8 @@
|
||||
"daoa",
|
||||
"dboundary",
|
||||
"EASA",
|
||||
"FADEC",
|
||||
"FCOM",
|
||||
"fuelflow",
|
||||
"GENERALENGINEDATA",
|
||||
"htail",
|
||||
@ -18,12 +20,14 @@
|
||||
"khofmann",
|
||||
"KHOFMANN",
|
||||
"maxangle",
|
||||
"maxcorrection",
|
||||
"otherwheel",
|
||||
"propwash",
|
||||
"simvar",
|
||||
"spoileron",
|
||||
"spoilerons",
|
||||
"steeringwheel",
|
||||
"stickyness",
|
||||
"TCDS",
|
||||
"TURBINEENGINEDATA",
|
||||
"vtail",
|
||||
|
||||
Loading…
x
Reference in New Issue
Block a user