// franconfig.cfg file // // Configuration file for the Engine and Plane Gauges - FS2002 // // F. Ouellette - Feb 2003 // // Version for Tom Gibson's version 6 panel with simplified variables // (no supercharger sections, no power or engine) // // ------------------------------------------------------------------- // This File configures the various parameters for planes // and is read by the 'Plane Gauge' that computes data in a common // database that gets read by other gauges. // ///////////////////////////////////////////////////////////////////// //////////////////////////// Planes ///////////////////////////////// // Each [planeNN] entry corresponds to a panel and a matching // 'FranPlaneTG!Type NN' gauge entry in the panel.cfg file. // It contains one or more// section for each plane model that use this same panel. // Before the first section we can put the values for the // 'engine' and 'cruise' values that apply by default to all models. // In the sections the 'model' will appear on the Clipboard. // The parameters in the first section are displayed at startup. // // Weights are in pounds, speeds in knots. // [plane01] plane_type = Douglas DC-6/6A/6B cruise = 1 climb_rate = 500 climb_fuelrate = 550 climb_speed = 175 descent_rate = 1000 descent_fuelrate = 350 descent_speed = 260 max_cruise_speed = 260 max_cruise_fuelrate = 460 lr_cruise_speed = 237 lr_cruise_fuelrate = 380 takeoff_taxi_fuel = 50 reserve_fuel = 285 electrical_system = on display = 0 model = Douglas DC-6B zero_fuel_wt = 74200 max_takeoff_wt = 103800 max_landing_wt = 88200 v1 = 83, 107 v2 = 103, 115 model = Douglas DC-6A zero_fuel_wt = 73930 max_takeoff_wt = 107000 max_landing_wt = 92360 v1 = 83, 107 v2 = 103, 115 model = Douglas DC-6 zero_fuel_wt = 67970 max_takeoff_wt = 87902 max_landing_wt = 73000 v1 = 77, 103 v2 = 95, 108 cruise = 2 [plane02] plane_type = Douglas DC-7/7B/7C cruise = 3 climb_rate = 600 climb_fuelrate = 600 climb_speed = 170 descent_rate = 1000 descent_fuelrate = 400 descent_speed = 255 max_cruise_speed = 285 max_cruise_fuelrate = 500 lr_cruise_speed = 245 lr_cruise_fuelrate = 450 takeoff_taxi_fuel = 50 reserve_fuel = 338 electrical_system = on display = 0 model = Douglas DC-7 zero_fuel_wt = 86370 max_takeoff_wt = 122202 max_landing_wt = 97000 v1 = 93, 118 v2 = 110, 125 model = DC-7B Domestic zero_fuel_wt = 88620 max_takeoff_wt = 124451 max_landing_wt = 102000 v1 = 92, 116 v2 = 110, 123 model = DC-7B PAA/SAA zero_fuel_wt = 84000 max_takeoff_wt = 126000 max_landing_wt = 102000 v1 = 92, 118 v2 = 110, 125 model = Douglas DC-7C zero_fuel_wt = 92000 max_takeoff_wt = 143000 max_landing_wt = 109000 v1 = 95, 118 v2 = 115, 125 cruise = 5 [plane03] plane_type = Convair/Martin Twins cruise = 6 climb_rate = 500 climb_fuelrate = 240 climb_speed = 165 descent_rate = 1000 descent_fuelrate = 180 descent_speed = 250 max_cruise_speed = 261 max_cruise_fuelrate = 230 lr_cruise_speed = 235 lr_cruise_fuelrate = 185 takeoff_taxi_fuel = 50 reserve_fuel = 150 electrical_system = on model = Convair CV-340 zero_fuel_wt = 36620 max_takeoff_wt = 47000 max_landing_wt = 46000 v1 = 96, 97 v2 = 98, 109 model = Martin 4-0-4 zero_fuel_wt = 36680 max_takeoff_wt = 44900 max_landing_wt = 43000 v1 = 90, 104 v2 = 103, 109 model = Convair CV-240 cruise = 7 zero_fuel_wt = 33100 max_takeoff_wt = 42400 max_landing_wt = 39800 v1 = 96, 97 v2 = 98, 109 model = Martin 2-0-2 cruise = 7 zero_fuel_wt = 33900 max_takeoff_wt = 39900 max_landing_wt = 38200 v1 = 90, 104 v2 = 103, 109 model = Convair CV-440 zero_fuel_wt = 37620 max_takeoff_wt = 48000 max_landing_wt = 47000 v1 = 96, 97 v2 = 98, 109 [plane04] plane_type = Canadair DC-4M/CL-2/CL-4 cruise = 2 climb_rate = 500 climb_fuelrate = 1000 climb_speed = 165 descent_rate = 1000 descent_fuelrate = 100 descent_speed = 260 max_cruise_speed = 278 max_cruise_fuelrate = 383 lr_cruise_speed = 264 lr_cruise_fuelrate = 327 takeoff_taxi_fuel = 50 reserve_fuel = 500 electrical_system = on model = Canadair CL-4 zero_fuel_wt = 57268 max_takeoff_wt = 79850 max_landing_wt = 72000 v1 = 77, 103 v2 = 95, 108 [end of planes] // Cruise table entries for the aircrafts // Entries with a '+' sign mean 'more than' the value they indicate // Altitude ranges are in INCREASING order, // weight in DECREASING order. // order is IAS, RPM, BMEP, BMEP Drop, FF, Blower [cruise1] cruise_name = Douglas DC-6A/6B weight_range = 100000+, 100000, 95000, 90000, 85000, 80000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 15000, 20000, 22000, 22000+ long_range_ceiling = 11000, 15000, 19000, 21000, 22000, 22000 alr1 = 208 1950 164 12 585 LO, 204 1900 158 12 455 LO, 199 1750 159 12 420 LO, 194 1600 160 12 380 LO, 189 1450 161 12 345 LO, 182 1400 153 12 315 LO alr2 = 206 2100 164 12 625 LO, 205 2000 162 12 480 LO, 198 1850 162 12 440 LO, 194 1700 162 12 400 LO, 189 1600 156 12 360 LO, 183 1550 149 12 330 LO alr3 = N/R, 205 2200 160 12 535 LO, 199 2100 155 12 490 LO, 194 1950 154 12 445 LO, 189 1850 148 12 410 LO, 183 1800 140 12 375 LO alr4 = N/R, N/R, 201 2200 160 12 565 HI, 196 2100 155 12 520 HI, 191 2150 140 12 475 LO, 185 2100 131 12 440 LO alr5 = N/R, N/R, N/R, 196 2300 152 12 580 HI, 191 2200 145 12 525 HI, 185 2150 136 12 485 HI alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ max_cruise_ceiling = 17000, 21000, 22000, 24000, 24000, 24000 amc1 = 221 2200 166 12 650 LO, 225 2200 166 12 650 LO, 229 2200 166 12 650 LO, 232 2200 166 12 650 LO, 236 2200 166 12 650 LO, 239 2200 166 12 650 LO amc2 = 215 2200 166 12 650 LO, 219 2200 166 12 650 LO, 223 2200 166 12 650 LO, 227 2200 166 12 650 LO, 230 2200 166 12 650 LO, 233 2200 166 12 650 LO amc3 = 207 2200 164 12 660 LO, 210 2200 164 12 660 LO, 216 2200 164 12 660 LO, 220 2200 164 12 660 LO, 224 2200 164 12 660 LO, 227 2200 164 12 660 LO amc4 = 194 2300 166 12 720 HI, 200 2300 166 12 670 HI, 206 2300 166 12 670 HI, 211 2300 166 12 670 HI, 215 2300 166 12 670 HI, 219 2300 166 12 670 HI amc5 = N/R, N/R, 192 2300 166 12 670 HI, 198 2300 166 12 670 HI, 204 2300 166 12 670 HI, 214 2300 166 12 670 HI amc6 = N/R, N/R, N/R, N/R, N/R, N/R // Three engine weight table 3_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 3_engine_ceiling = 6000, 8000, 12000, 16000, 18000, 18000 a31 = 208 2150 186 12 1030 LO, 204 2000 186 12 915 LO, 199 2250 165 12 695 LO, 194 2100 162 12 640 LO, 189 1900 164 12 590 LO, 182 1700 167 12 540 LO a32 = 206 2100 186 12 1040 LO, 205 2000 188 12 940 LO, 198 2300 165 12 760 LO, 194 2200 159 12 740 LO, 189 2000 165 12 610 LO, 183 1800 169 12 580 LO a33 = N/R, N/R, 199 2350 165 12 1020 LO, 194 2300 165 12 915 LO, 189 2150 164 12 660 LO, 183 1950 164 12 605 LO a34 = N/R, N/R, N/R, 195 2300 166 12 1010 HI, 190 2300 163 12 705 LO, 184 2200 156 12 650 LO a35 = N/R, N/R, N/R, 196 2300 170 12 1050 HI, 191 2250 163 12 940 HI, 185 2200 164 12 690 HI a36 = N/R, N/R, N/R, N/R, N/R, N/R // Two engine weight table 2_engine_alt_range = 1000, 2000, 4000, 6000, 8000, 8000+ 2_engine_ceiling = 1, 1, 2000, 8000, 8000, 8000 a21 = N/R, N/R, 193 2600 206 12 930 LO, 187 2400 203 12 700 LO, 184 2300 201 12 650 LO, 177 2090 202 12 500 LO a22 = N/R, N/R, 190 2600 207 12 940 LO, 187 2450 201 12 740 LO, 184 2300 204 12 670 LO, 177 2020 205 12 520 LO a23 = N/R, N/R, N/R, 187 2600 200 12 840 LO, 184 2400 201 12 790 LO, 177 2150 202 12 575 LO a24 = N/R, N/R, N/R, 187 2600 202 12 895 LO, 184 2500 199 12 770 LO, 176 2200 203 12 680 LO a25 = N/R, N/R, N/R, 186 2600 207 12 940 LO, 184 2600 198 12 755 LO, 177 2400 192 12 720 LO a26 = N/R, N/R, N/R, N/R, N/R, N/R [cruise2] plane_name = Douglas DC-6 weight_range = 85000+, 85000, 80000, 75000, 70000, 65000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 15000, 20000, 22000, 22000+ long_range_ceiling = 11000, 15000, 19000, 21000, 22000, 22000 alr1 = N/R, 199 1750 159 12 400 LO, 194 1600 160 12 360 LO, 189 1450 161 12 325 LO, 182 1400 153 12 295 LO, 177 1400 140 12 275 LO alr2 = N/R, 198 1850 162 12 435 LO, 194 1700 162 12 395 LO, 189 1600 156 12 355 LO, 183 1550 149 12 325 LO, 177 1500 143 12 305 LO alr3 = N/R, 199 2100 155 12 480 LO, 194 1950 154 12 435 LO, 189 1850 148 12 400 LO, 183 1800 140 12 365 LO, 177 1700 135 12 330 LO alr4 = N/R, 201 2200 160 12 540 HI, 196 2100 155 12 495 HI, 191 2150 140 12 450 LO, 185 2100 131 12 415 LO, 179 1950 128 12 370 LO alr5 = N/R, N/R, 196 2300 152 12 550 HI, 191 2200 145 12 495 HI, 185 2150 136 12 455 HI, 180 2100 127 12 415 HI alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ max_cruise_ceiling = 20000, 24000, 24000, 24000, 24000, 24000 amc1 = N/R, 219 2100 160 12 650 LO, 223 2100 160 12 650 LO, 226 2100 160 12 650 LO, 227 2100 160 12 650 LO, 229 2100 160 12 650 LO amc2 = N/R, 212 2100 160 12 650 LO, 217 2100 160 12 650 LO, 221 2100 160 12 650 LO, 222 2100 160 12 650 LO, 223 2100 160 12 650 LO amc3 = N/R, 202 2100 156 12 650 LO, 208 2100 156 12 650 LO, 213 2100 156 12 650 LO, 215 2100 156 12 650 LO, 216 2100 156 12 650 LO amc4 = N/R, 195 2200 156 12 670 HI, 202 2200 156 12 670 HI, 207 2200 156 12 670 HI, 210 2200 156 12 670 HI, 212 2100 156 12 670 HI amc5 = N/R, N/R, 183 2200 147 12 670 HI, 188 2200 147 12 670 HI, 193 2200 147 12 670 HI, 197 2200 147 12 670 HI amc6 = N/R, N/R, N/R, N/R, N/R, N/R // Three engine weight table 3_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 3_engine_ceiling = 1, 12000, 16000, 18000, 18000, 18000 a31 = N/R, 199 2250 165 12 555 LO, 194 2100 162 12 500 LO, 189 1900 164 12 450 LO, 182 1700 167 12 400 LO, 177 1550 166 12 360 LO a32 = N/R, 198 2300 165 12 620 LO, 194 2200 159 12 600 LO, 189 2000 165 12 470 LO, 183 1800 169 12 440 LO, 177 1770 162 12 390 LO a33 = N/R, 199 2350 165 12 880 LO, 194 2300 165 12 775 LO, 189 2150 164 12 520 LO, 183 1950 164 12 465 LO, 177 1850 157 12 420 LO a34 = N/R, N/R, 195 2300 166 12 870 HI, 190 2300 163 12 565 LO, 184 2200 156 12 510 LO, 178 2100 149 12 460 LO a35 = N/R, N/R, 196 2300 170 12 910 HI, 191 2250 163 12 800 HI, 185 2200 164 12 550 HI, 179 2300 143 12 500 LO a36 = N/R, N/R, N/R, N/R, N/R, N/R // Two engine weight table 2_engine_alt_range = 1000, 2000, 4000, 6000, 8000, 8000+ 2_engine_ceiling = 1, 1000, 2000, 8000, 8000, 8000 a21 = N/R, 193 2600 206 12 1430 LO, 187 2400 203 12 1200 LO, 184 2300 201 12 1100 LO, 177 2090 202 12 900 LO, 174 1950 201 12 815 LO a22 = N/R, 190 2600 207 12 1440 LO, 187 2450 201 12 1240 LO, 184 2300 204 12 1120 LO, 177 2020 205 12 920 LO, 174 1950 204 12 830 LO a23 = N/R, N/R, 187 2600 200 12 1340 LO, 184 2400 201 12 1190 LO, 177 2150 202 12 975 LO, 174 2050 200 12 890 LO a24 = N/R, N/R, 187 2600 202 12 1395 LO, 184 2500 199 12 1270 LO, 176 2200 203 12 1030 LO, 174 2100 201 12 935 LO a25 = N/R, N/R, 186 2600 207 12 1440 LO, 184 2600 198 12 1255 LO, 177 2400 192 12 1120 LO, 174 2300 189 12 1015 LO a26 = N/R, N/R, N/R, N/R, N/R, N/R [cruise3] cruise_name = Douglas DC-7/DC-7B weight_range = 122000+, 122000, 116000, 110000, 104000, 98000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 14000, 19000, 23000, 23000+ long_range_ceiling = 14000, 19000, 21000, 23000, 23000, 23000 alr1 = 223 2200 154 15 615 LO, 218 2050 153 15 570 LO, 213 1950 149 15 525 LO, 208 1800 143 14 465 LO, 202 1650 142 14 425 LO, 196 1600 138 14 390 LO alr2 = 224 2350 156 16 655 LO, 219 2200 154 15 600 LO, 213 2100 149 15 560 LO, 208 1950 147 15 510 LO, 202 1850 142 14 460 LO, 196 1750 136 14 420 LO alr3 = 225 2400 167 17 740 HI, 219 2400 153 15 645 LO, 214 2350 144 14 605 LO, 208 2300 135 14 565 LO, 203 2200 129 13 520 LO, 197 2100 123 12 470 LO alr4 = N/R, 220 2400 169 16 740 HI, 214 2350 158 16 680 HI, 209 2300 147 15 630 HI, 203 2150 129 13 575 LO, 197 2100 119 12 535 LO alr5 = N/R, N/R, 210 2400 164 16 720 HI, 206 2400 156 16 670 HI, 200 2300 154 15 615 HI, 195 2200 153 15 575 HI alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 25000, 25000+ max_cruise_ceiling = 20000, 27000, 28000, 28000, 28000, 28000 amc1 = 245 2400 182 18 770 LO, 249 2400 182 18 770 LO, 252 2400 182 18 770 LO, 254 2400 182 18 770 LO, 255 2400 182 18 770 LO, 257 2400 182 18 770 LO amc2 = 239 2400 185 18 770 LO, 243 2400 185 18 770 LO, 245 2400 185 18 770 LO, 245 2400 185 18 770 LO, 246 2400 185 18 770 LO, 249 2400 185 18 770 LO amc3 = 233 2400 188 18 770 LO, 237 2400 188 18 770 LO, 238 2400 188 18 770 LO, 241 2400 188 18 770 LO, 242 2400 188 18 770 LO, 253 2400 188 18 770 LO amc4 = 218 2400 175 17 750 HI, 225 2400 175 17 750 HI, 226 2400 175 17 750 HI, 232 2400 175 17 750 HI, 236 2400 175 17 750 HI, 238 2400 175 17 750 HI amc5 = N/R, 218 2400 177 18 750 HI, 222 2400 177 18 750 HI, 228 2400 177 18 750 HI, 232 2400 177 18 750 HI, 234 2400 177 18 750 HI amc6 = N/R, 191 2400 177 18 750 HI, 194 2400 177 18 750 HI, 205 2400 177 18 750 HI, 214 2400 177 18 750 HI, 221 2400 177 18 750 HI // Three engine weight table 3_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 3_engine_ceiling = 1, 12000, 16000, 18000, 18000, 18000 a31 = N/R, 223 2500 185 19 1195 LO, 218 2400 177 18 770 LO, 213 2400 165 17 720 LO, 207 2300 158 16 665 LO, 202 2150 154 16 605 LO a32 = N/R, 224 2500 197 20 1275 LO, 219 2500 182 19 1140 LO, 212 2400 158 16 750 LO, 208 2400 161 16 695 LO, 202 2250 156 16 630 LO a33 = N/R, 224 2600 204 20 1540 LO, 219 2500 194 19 1220 LO, 189 2150 164 12 520 LO, 183 1950 164 12 465 LO, 177 1850 157 12 420 LO a34 = N/R, N/R, 195 2300 166 12 870 HI, 190 2300 163 12 565 LO, 184 2200 156 12 510 LO, 178 2100 149 12 460 LO a35 = N/R, N/R, 196 2300 170 12 910 HI, 191 2250 163 12 800 HI, 185 2200 164 12 550 HI, 179 2300 143 12 500 LO a36 = N/R, N/R, N/R, N/R, N/R, N/R // Two engine weight table 2_engine_alt_range = 1000, 2000, 4000, 6000, 8000, 8000+ 2_engine_ceiling = 1, 1, 5000, 5000, 6000, 8000 a21 = N/R, N/R, 211 2600 246 25 1810 LO, 213 2600 237 24 1735 LO, 207 2600 217 22 1535 LO, 201 2600 199 20 1350 LO a22 = N/R, N/R, 209 2600 247 25 1810 LO, 210 2600 238 24 1730 LO, 207 2600 221 22 1560 LO, 202 2600 202 20 1370 LO a23 = N/R, N/R, 205 2600 248 25 1815 LO, 207 2600 239 24 1725 LO, 208 2600 228 23 1615 LO, 202 2600 208 21 1410 LO a24 = N/R, N/R, N/R, N/R, 208 2600 234 24 1660 LO, 202 2600 214 22 1460 LO a25 = N/R, N/R, N/R, N/R, N/R, 202 2600 221 22 1510 LO a26 = N/R, N/R, N/R, N/R, N/R, N/R [cruise4] cruise_name = Douglas DC-7B Overwater weight_range = 122000+, 122000, 116000, 110000, 104000, 98000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 14000, 19000, 23000, 23000+ long_range_ceiling = 14000, 19000, 21000, 23000, 23000, 23000 alr1 = 223 2200 154 15 615 LO, 218 2050 153 15 570 LO, 213 1950 149 15 525 LO, 208 1800 143 14 465 LO, 202 1650 142 14 425 LO, 196 1600 138 14 390 LO alr2 = 224 2350 156 16 655 LO, 219 2200 154 15 600 LO, 213 2100 149 15 560 LO, 208 1950 147 15 510 LO, 202 1850 142 14 460 LO, 196 1750 136 14 420 LO alr3 = 225 2400 167 17 740 HI, 219 2400 153 15 645 LO, 214 2350 144 14 605 LO, 208 2300 135 14 565 LO, 203 2200 129 13 520 LO, 197 2100 123 12 470 LO alr4 = N/R, 220 2400 169 16 740 HI, 214 2350 158 16 680 HI, 209 2300 147 15 630 HI, 203 2150 129 13 575 LO, 197 2100 119 12 535 LO alr5 = N/R, N/R, 210 2400 164 16 720 HI, 206 2400 156 16 670 HI, 200 2300 154 15 615 HI, 195 2200 153 15 575 HI alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 25000, 25000+ max_cruise_ceiling = 20000, 27000, 28000, 28000, 28000, 28000 amc1 = 250 2400 182 18 770 LO, 254 2400 182 18 770 LO, 257 2400 182 18 770 LO, 260 2400 182 18 770 LO, 262 2400 182 18 770 LO, 265 2400 182 18 770 LO amc2 = 244 2400 185 18 770 LO, 248 2400 185 18 770 LO, 252 2400 185 18 770 LO, 258 2400 185 18 770 LO, 258 2400 185 18 770 LO, 260 2400 185 18 770 LO amc3 = 240 2400 188 18 770 LO, 244 2400 188 18 770 LO, 247 2400 188 18 770 LO, 250 2400 188 18 770 LO, 253 2400 188 18 770 LO, 256 2400 188 18 770 LO amc4 = 218 2400 175 17 750 HI, 225 2400 175 17 750 HI, 229 2400 175 17 750 HI, 234 2400 175 17 750 HI, 238 2400 175 17 750 HI, 241 2400 175 17 750 HI amc5 = N/R, 221 2400 177 18 750 HI, 227 2400 177 18 750 HI, 232 2400 177 18 750 HI, 237 2400 177 18 750 HI, 241 2400 177 18 750 HI amc6 = N/R, 191 2400 177 18 750 HI, 194 2400 177 18 750 HI, 205 2400 177 18 750 HI, 214 2400 177 18 750 HI, 221 2400 177 18 750 HI // Three engine weight table 3_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 3_engine_ceiling = 1, 12000, 16000, 18000, 18000, 18000 a31 = N/R, 223 2500 185 19 1195 LO, 218 2400 177 18 770 LO, 213 2400 165 17 720 LO, 207 2300 158 16 665 LO, 202 2150 154 16 605 LO a32 = N/R, 224 2500 197 20 1275 LO, 219 2500 182 19 1140 LO, 212 2400 158 16 750 LO, 208 2400 161 16 695 LO, 202 2250 156 16 630 LO a33 = N/R, 224 2600 204 20 1540 LO, 219 2500 194 19 1220 LO, 189 2150 164 12 520 LO, 183 1950 164 12 465 LO, 177 1850 157 12 420 LO a34 = N/R, N/R, 195 2300 166 12 870 HI, 190 2300 163 12 565 LO, 184 2200 156 12 510 LO, 178 2100 149 12 460 LO a35 = N/R, N/R, 196 2300 170 12 910 HI, 191 2250 163 12 800 HI, 185 2200 164 12 550 HI, 179 2300 143 12 500 LO a36 = N/R, N/R, N/R, N/R, N/R, N/R // Two engine weight table 2_engine_alt_range = 1000, 2000, 4000, 6000, 8000, 8000+ 2_engine_ceiling = 1, 1, 5000, 5000, 6000, 8000 a21 = N/R, N/R, 211 2600 246 25 1810 LO, 213 2600 237 24 1735 LO, 207 2600 217 22 1535 LO, 201 2600 199 20 1350 LO a22 = N/R, N/R, 209 2600 247 25 1810 LO, 210 2600 238 24 1730 LO, 207 2600 221 22 1560 LO, 202 2600 202 20 1370 LO a23 = N/R, N/R, 205 2600 248 25 1815 LO, 207 2600 239 24 1725 LO, 208 2600 228 23 1615 LO, 202 2600 208 21 1410 LO a24 = N/R, N/R, N/R, N/R, 208 2600 234 24 1660 LO, 202 2600 214 22 1460 LO a25 = N/R, N/R, N/R, N/R, N/R, 202 2600 221 22 1510 LO a26 = N/R, N/R, N/R, N/R, N/R, N/R [cruise5] cruise_name = DC-7C weight_range = 127000+, 127000, 121000, 115000, 109000, 103000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 14000, 19000, 23000, 23000+ long_range_ceiling = 14000, 19000, 21000, 23000, 23000, 23000 alr1 = 223 2200 154 15 615 LO, 218 2050 153 15 570 LO, 213 1950 149 15 525 LO, 208 1800 143 14 465 LO, 202 1650 142 14 425 LO, 196 1600 138 14 390 LO alr2 = 224 2350 156 16 655 LO, 219 2200 154 15 600 LO, 213 2100 149 15 560 LO, 208 1950 147 15 510 LO, 202 1850 142 14 460 LO, 196 1750 136 14 420 LO alr3 = 225 2400 167 17 740 HI, 219 2400 153 15 645 LO, 214 2350 144 14 605 LO, 208 2300 135 14 565 LO, 203 2200 129 13 520 LO, 197 2100 123 12 470 LO alr4 = N/R, 220 2400 169 16 740 HI, 214 2350 158 16 680 HI, 209 2300 147 15 630 HI, 203 2150 129 13 575 LO, 197 2100 119 12 535 LO alr5 = N/R, N/R, 210 2400 164 16 720 HI, 206 2400 156 16 670 HI, 200 2300 154 15 615 HI, 195 2200 153 15 575 HI alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 25000, 25000+ max_cruise_ceiling = 20000, 27000, 28000, 28000, 28000, 28000 amc1 = 230 2400 182 18 770 LO, 239 2400 182 18 770 LO, 243 2400 182 18 770 LO, 246 2400 182 18 770 LO, 247 2400 182 18 770 LO, 250 2400 182 18 770 LO amc2 = 224 2400 185 18 770 LO, 228 2400 185 18 770 LO, 233 2400 185 18 770 LO, 235 2400 185 18 770 LO, 238 2400 185 18 770 LO, 242 2400 185 18 770 LO amc3 = 213 2400 188 18 770 LO, 219 2400 188 18 770 LO, 223 2400 188 18 770 LO, 229 2400 188 18 770 LO, 231 2400 188 18 770 LO, 243 2400 188 18 770 LO amc4 = 196 2400 175 17 750 HI, 204 2400 175 17 750 HI, 211 2400 175 17 750 HI, 218 2400 175 17 750 HI, 223 2400 175 17 750 HI, 228 2400 175 17 750 HI amc5 = N/R, 198 2400 177 18 750 HI, 206 2400 177 18 750 HI, 214 2400 177 18 750 HI, 219 2400 177 18 750 HI, 224 2400 177 18 750 HI amc6 = N/R, 188 2400 177 18 750 HI, 190 2400 177 18 750 HI, 201 2400 177 18 750 HI, 210 2400 177 18 750 HI, 217 2400 177 18 750 HI // Three engine weight table 3_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 3_engine_ceiling = 1, 12000, 16000, 18000, 18000, 18000 a31 = N/R, 223 2500 185 19 1195 LO, 218 2400 177 18 770 LO, 213 2400 165 17 720 LO, 207 2300 158 16 665 LO, 202 2150 154 16 605 LO a32 = N/R, 224 2500 197 20 1275 LO, 219 2500 182 19 1140 LO, 212 2400 158 16 750 LO, 208 2400 161 16 695 LO, 202 2250 156 16 630 LO a33 = N/R, 224 2600 204 20 1540 LO, 219 2500 194 19 1220 LO, 189 2150 164 12 520 LO, 183 1950 164 12 465 LO, 177 1850 157 12 420 LO a34 = N/R, N/R, 195 2300 166 12 870 HI, 190 2300 163 12 565 LO, 184 2200 156 12 510 LO, 178 2100 149 12 460 LO a35 = N/R, N/R, 196 2300 170 12 910 HI, 191 2250 163 12 800 HI, 185 2200 164 12 550 HI, 179 2300 143 12 500 LO a36 = N/R, N/R, N/R, N/R, N/R, N/R // Two engine weight table 2_engine_alt_range = 1000, 2000, 4000, 6000, 8000, 8000+ 2_engine_ceiling = 1, 1, 5000, 5000, 6000, 8000 a21 = N/R, N/R, 211 2600 246 25 1810 LO, 213 2600 237 24 1735 LO, 207 2600 217 22 1535 LO, 201 2600 199 20 1350 LO a22 = N/R, N/R, 209 2600 247 25 1810 LO, 210 2600 238 24 1730 LO, 207 2600 221 22 1560 LO, 202 2600 202 20 1370 LO a23 = N/R, N/R, 205 2600 248 25 1815 LO, 207 2600 239 24 1725 LO, 208 2600 228 23 1615 LO, 202 2600 208 21 1410 LO a24 = N/R, N/R, N/R, N/R, 208 2600 234 24 1660 LO, 202 2600 214 22 1460 LO a25 = N/R, N/R, N/R, N/R, N/R, 202 2600 221 22 1510 LO a26 = N/R, N/R, N/R, N/R, N/R, N/R [cruise6] cruise_name = Convair 340/Martin 404 Twins weight_range = 45000+, 45000, 40000, 35000, 30000, 25000 // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ long_range_ceiling = 11000, 15000, 19000, 20000, 20000, 20000 alr1 = 208 1950 164 12 595 LO, 204 1900 158 12 565 LO, 199 1750 159 12 530 LO, 194 1600 160 12 490 LO, 189 1450 161 12 455 LO, 182 1400 153 12 425 LO alr2 = 206 2100 164 12 640 LO, 205 2000 162 12 605 LO, 198 1850 162 12 565 LO, 194 1700 162 12 525 LO, 189 1600 156 12 485 LO, 183 1550 149 12 455 LO alr3 = N/R, 205 2200 160 12 655 LO, 199 2100 155 12 610 LO, 194 1950 154 12 565 LO, 189 1850 148 12 530 LO, 183 1800 140 12 495 LO alr4 = N/R, N/R, 201 2200 160 12 670 HI, 196 2100 155 12 625 HI, 191 2150 140 12 580 LO, 185 2100 131 12 545 LO alr5 = N/R, N/R, N/R, N/R, N/R, N/R alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ max_cruise_ceiling = 20000, 20000, 20000, 20000, 20000, 20000 amc1 = 213 2100 164 12 620 LO, 219 2100 164 12 620 LO, 223 2100 164 12 630 LO, 226 2100 164 12 630 LO, 229 2100 164 12 620 LO, 231 2100 164 12 620 LO amc2 = 207 2100 164 12 620 LO, 212 2100 164 12 620 LO, 217 2100 164 12 630 LO, 221 2100 164 12 630 LO, 224 2100 164 12 620 LO, 227 2100 164 12 620 LO amc3 = 196 2100 164 12 620 LO, 202 2100 160 12 620 LO, 208 2100 160 12 630 LO, 213 2100 160 12 630 LO, 217 2100 160 12 620 LO, 220 2100 160 12 620 LO amc4 = 189 2200 164 12 620 HI, 191 2200 160 12 620 HI, 197 2200 160 12 630 HI, 202 2200 160 12 630 HI, 206 2200 160 12 630 HI, 211 2100 160 12 620 HI amc5 = N/R, N/R, N/R, N/R, N/R, N/R amc6 = N/R, N/R, N/R, N/R, N/R, N/R // One engine weight table 1_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 1_engine_ceiling = 6000, 8000, 12000, 16000, 18000, 18000 a11 = 193 2600 206 12 1230 LO, 193 2600 206 12 1230 LO, 187 2400 203 12 1000 LO, 184 2300 201 12 900 LO, 177 2090 202 12 800 LO, 174 1950 201 12 715 LO a12 = 190 2600 207 12 1220 LO, 190 2600 207 12 1040 LO, 187 2450 201 12 1040 LO, 184 2300 204 12 920 LO, 177 2020 205 12 820 LO, 174 1950 204 12 730 LO a13 = N/R, N/R, 187 2600 200 12 1140 LO, 184 2400 201 12 1090 LO, 177 2150 202 12 875 LO, 174 2050 200 12 790 LO a14 = N/R, N/R, N/R, 184 2500 199 12 1070 LO, 176 2200 203 12 930 LO, 174 2100 201 12 835 LO a15 = N/R, N/R, N/R, N/R, 177 2400 192 12 1020 LO, 174 2300 189 12 915 LO a16 = N/R, N/R, N/R, N/R, N/R, N/R [cruise7] cruise_name = Convair 240/Martin 202 Twins weight_range = 45000+, 45000, 40000, 35000, 30000, 25000 // Across = decreasing weight, down = increasing altitude // Long range weight table // Across = decreasing weight, down = increasing altitude // Long range weight table long_range_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ long_range_ceiling = 11000, 15000, 19000, 20000, 20000, 20000 alr1 = 218 1950 164 12 595 LO, 214 1900 158 12 565 LO, 209 1750 159 12 530 LO, 204 1600 160 12 490 LO, 199 1450 161 12 455 LO, 192 1400 153 12 425 LO alr2 = 216 2100 164 12 640 LO, 215 2000 162 12 605 LO, 208 1850 162 12 565 LO, 204 1700 162 12 525 LO, 199 1600 156 12 485 LO, 193 1550 149 12 455 LO alr3 = N/R, 215 2200 160 12 655 LO, 209 2100 155 12 610 LO, 204 1950 154 12 565 LO, 199 1850 148 12 530 LO, 193 1800 140 12 495 LO alr4 = N/R, N/R, 201 2200 160 12 670 HI, 206 2100 155 12 625 HI, 201 2150 140 12 580 LO, 195 2100 131 12 545 LO alr5 = N/R, N/R, N/R, N/R, N/R, N/R alr6 = N/R, N/R, N/R, N/R, N/R, N/R // Max cruise weight table max_cruise_alt_range = 5000, 10000, 15000, 20000, 24000, 24000+ max_cruise_ceiling = 20000, 20000, 20000, 20000, 20000, 20000 amc1 = 223 2100 164 12 620 LO, 229 2100 164 12 620 LO, 233 2100 164 12 630 LO, 236 2100 164 12 630 LO, 239 2100 164 12 620 LO, 241 2100 164 12 620 LO amc2 = 217 2100 164 12 620 LO, 222 2100 164 12 620 LO, 227 2100 164 12 630 LO, 231 2100 164 12 630 LO, 234 2100 164 12 620 LO, 237 2100 164 12 620 LO amc3 = 206 2100 164 12 620 LO, 212 2100 160 12 620 LO, 218 2100 160 12 630 LO, 223 2100 160 12 630 LO, 227 2100 160 12 620 LO, 230 2100 160 12 620 LO amc4 = 199 2200 164 12 620 HI, 201 2200 160 12 620 HI, 207 2200 160 12 630 HI, 212 2200 160 12 630 HI, 216 2200 160 12 630 HI, 221 2100 160 12 620 HI amc5 = N/R, N/R, N/R, N/R, N/R, N/R amc6 = N/R, N/R, N/R, N/R, N/R, N/R // One engine weight table 1_engine_alt_range = 4000, 8000, 12000, 16000, 18000, 18000+ 1_engine_ceiling = 6000, 8000, 12000, 16000, 18000, 18000 a11 = 203 2600 206 12 1230 LO, 203 2600 206 12 1230 LO, 197 2400 203 12 1000 LO, 194 2300 201 12 900 LO, 187 2090 202 12 800 LO, 184 1950 201 12 715 LO a12 = 200 2600 207 12 1220 LO, 200 2600 207 12 1040 LO, 197 2450 201 12 1040 LO, 194 2300 204 12 920 LO, 187 2020 205 12 820 LO, 184 1950 204 12 730 LO a13 = N/R, N/R, 197 2600 200 12 1140 LO, 194 2400 201 12 1090 LO, 187 2150 202 12 875 LO, 184 2050 200 12 790 LO a14 = N/R, N/R, N/R, 194 2500 199 12 1070 LO, 186 2200 203 12 930 LO, 184 2100 201 12 835 LO a15 = N/R, N/R, N/R, N/R, 187 2400 192 12 1020 LO, 184 2300 189 12 915 LO a16 = N/R, N/R, N/R, N/R, N/R, N/R [end of file]
