? Generating manoeuvre sequence from 'range' calculations... Summary of segments in the sequence: ----------------------------------------------- Seg. Speed mode Thrust mode Stop condition 1. v3 at-%mto to alt 1500. 2. specify-cas at-%mcl to alt 10000. 3. specify-cas at-%mcl to mach 0.80 4. same-mach at-%mcl to alt 41000. 5. specify-mach level-cruise to next stepup 6. same-mach at-%mcl to dalt ±4000. 7. same-mach level-cruise to next stepup 8. same-mach at-%mcl to dalt ±4000. 9. same-mach level-cruise to next stepup 10. same-mach at-%mcl to dalt ±2000. 11. same-mach level-cruise to mass 53242. 12. specify-mach at-idle to cas 277. 13. specify-cas at-idle to alt 10000. 14. specify-cas at-idle to alt 1500. 15. vapp match-grad to alt 50. ----------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 1 starts at: Initial Mass 90739. lb. (CL 0.93 trapezoidal) Initial Altitude 35. feet Delta-ISA +0. deg.C Airspeed (CAS) 159. kts (V3) Flaps 15 deg. Undercarriage up All eng.operative Thrust per engine 12381. lbf. (100% MTO) Climb/Descent rate 3128. feet/min Flightpath angle 11.0 deg. (grad.19.43%) True airspeed 159. kts Fuel Flow rate 12520. lb/hr NOx emission rate 270.4 lb/hr HC emission rate 0.251 lb/hr CO emission rate 14.0 lb/hr L/D ratio 13.83 Total aircraft drag 6560. lbf. Segment 1 ends at total time = 0.5 mins, endmass = 90642.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +1465. +28.4 +0.00 +97.3 +2.09 +0.002 +0.11 Final : 1500. 28.4 0.00 97.3 2.09 0.002 0.11 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 35. 0.0 0.000 0.0 12381. 159. 0.240 3128. 6560. 159. 198. 3.1 0.000 10.9 12338. 159. 0.241 3121. 6560. 159. 361. 6.3 0.000 21.7 12296. 159. 0.242 3113. 6559. 160. 523. 9.4 0.000 32.5 12253. 159. 0.242 3106. 6558. 160. 686. 12.5 0.000 43.3 12211. 159. 0.243 3098. 6557. 160. 849. 15.7 0.000 54.2 12168. 159. 0.244 3090. 6556. 161. 1012. 18.9 0.000 65.0 12126. 159. 0.244 3083. 6555. 161. 1174. 22.0 0.000 75.7 12084. 159. 0.245 3075. 6555. 162. 1337. 25.2 0.000 86.5 12041. 159. 0.246 3067. 6554. 162. 1500. 28.4 0.000 97.3 11999. 159. 0.247 3059. 6553. 162. ----------------------------------------------------------------------------- Acceleration to 250.kts in level flight at 1500.feet =0.20g: Time +24.6 sec, Dist +1.44 n.miles, Fuelburn +83.9 lb. NOx +1.83 lb., HC +0.002 lb., CO +0.096 lb. ----------------------------------------------------------------------------- Manoeuvre segment 2 starts at: Initial Mass 90558. lb. (CL 0.38 trapezoidal) Initial Altitude 1500. feet Delta-ISA +0. deg.C Airspeed (CAS) 250. kts (input) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 9172. lbf. (100% MCL) Climb/Descent rate 3525. feet/min Flightpath angle 7.8 deg. (grad.13.63%) True airspeed 255. kts Fuel Flow rate 10565. lb/hr NOx emission rate 193.5 lb/hr HC emission rate 0.216 lb/hr CO emission rate 11.1 lb/hr L/D ratio 18.14 Total aircraft drag 4991. lbf. Segment 2 ends at total time = 3.5 mins, endmass = 90139.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +8500. +155. +11.68 +419.2 +7.42 +0.009 +0.46 Final : 10000. 208. 13.12 600.4 11.34 0.013 0.66 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 1500. 53.0 1.436 181.2 9172. 250. 0.388 3525. 4991. 255. 1947. 60.7 1.980 203.5 9091. 250. 0.391 3502. 4991. 257. 2395. 68.4 2.531 225.8 9012. 250. 0.394 3478. 4990. 259. 2842. 76.1 3.089 248.1 8933. 250. 0.397 3455. 4990. 260. 3289. 83.9 3.654 270.3 8855. 250. 0.400 3432. 4989. 262. 3737. 91.7 4.226 292.5 8784. 250. 0.404 3412. 4989. 264. 4184. 99.6 4.806 314.6 8713. 250. 0.407 3392. 4988. 265. 4632. 107.6 5.393 336.7 8642. 250. 0.410 3372. 4987. 267. 5079. 115.6 5.987 358.8 8570. 250. 0.413 3351. 4987. 269. 5526. 123.6 6.589 380.9 8491. 250. 0.417 3325. 4986. 270. 5974. 131.7 7.200 402.9 8412. 250. 0.420 3299. 4985. 272. 6421. 139.9 7.819 424.9 8333. 250. 0.424 3273. 4985. 274. 6868. 148.1 8.448 446.9 8255. 250. 0.427 3247. 4984. 276. 7316. 156.4 9.086 468.8 8178. 250. 0.431 3221. 4983. 278. 7763. 164.8 9.733 490.8 8100. 250. 0.434 3194. 4982. 279. 8211. 173.2 10.39 512.7 8023. 250. 0.438 3168. 4981. 281. 8658. 181.7 11.06 534.7 7947. 250. 0.441 3141. 4981. 283. 9105. 190.3 11.73 556.6 7871. 250. 0.445 3114. 4980. 285. 9553. 199.0 12.42 578.5 7795. 250. 0.449 3087. 4979. 287. 10000. 207.7 13.12 600.4 7720. 250. 0.452 3060. 4978. 289. ----------------------------------------------------------------------------- Acceleration to 277.kts in level flight at 10000.feet =0.13g: Time +11.9 sec, Dist +1.01 n.miles, Fuelburn +33.8 lb. NOx +0.67 lb., HC +0.001 lb., CO +0.042 lb. ----------------------------------------------------------------------------- Manoeuvre segment 3 starts at: Initial Mass 90105. lb. (CL 0.31 trapezoidal) Initial Altitude 10000. feet Delta-ISA +0. deg.C Airspeed (CAS) 277. kts (input) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 7489. lbf. (100% MCL) Climb/Descent rate 3036. feet/min Flightpath angle 5.4 deg. (grad.9.40%) True airspeed 319. kts Fuel Flow rate 9055. lb/hr NOx emission rate 156.4 lb/hr HC emission rate 0.210 lb/hr CO emission rate 10.4 lb/hr L/D ratio 16.69 Total aircraft drag 5399. lbf. Segment 3 ends at total time = 15.8 mins, endmass = 88736.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +24040. +730. +80.27 +1369.1 +19.69 +0.041 +2.06 Final : 34040. 949. 94.40 2003.4 31.70 0.054 2.76 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 10000. 219.6 14.13 634.2 7489. 277. 0.500 3036. 5399. 319. 11265. 245.0 16.40 697.2 7279. 277. 0.512 2946. 5393. 325. 12531. 271.2 18.79 760.5 7071. 277. 0.524 2854. 5386. 331. 13796. 298.2 21.30 824.0 6865. 277. 0.536 2761. 5379. 337. 15061. 326.2 23.95 888.0 6663. 277. 0.549 2666. 5371. 344. 16326. 355.3 26.75 952.6 6456. 277. 0.562 2565. 5362. 350. 17592. 385.5 29.72 1018.0 6252. 277. 0.576 2463. 5353. 357. 18857. 417.0 32.87 1084.3 6053. 277. 0.590 2361. 5343. 364. 20122. 449.8 36.23 1151.6 5863. 277. 0.604 2261. 5333. 371. 21387. 484.1 39.80 1219.9 5685. 277. 0.619 2168. 5321. 378. 22653. 519.9 43.60 1289.4 5511. 277. 0.635 2074. 5309. 386. 23918. 557.4 47.66 1360.1 5340. 277. 0.651 1980. 5296. 393. 25183. 596.7 52.00 1432.2 5171. 277. 0.667 1884. 5282. 401. 26448. 638.1 56.66 1506.0 5002. 277. 0.684 1786. 5267. 409. 27714. 681.9 61.68 1581.7 4837. 277. 0.701 1688. 5251. 417. 28979. 728.2 67.11 1659.6 4677. 277. 0.719 1591. 5237. 426. 30244. 777.5 73.00 1740.1 4521. 277. 0.738 1493. 5222. 434. 31509. 830.2 79.43 1823.6 4364. 277. 0.757 1391. 5211. 443. 32775. 887.1 86.50 1910.9 4210. 277. 0.777 1283. 5213. 452. 34040. 949.2 94.40 2003.4 4061. 277. 0.797 1165. 5244. 461. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 4 starts at: Initial Mass 88736. lb. (CL 0.34 trapezoidal) Initial Altitude 34040. feet Delta-ISA +0. deg.C Airspeed (CAS) 277. kts (fixed Mach 0.797) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 4061. lbf. (100% MCL) Climb/Descent rate 1656. feet/min Flightpath angle 2.0 deg. (grad.3.54%) True airspeed 461. kts Fuel Flow rate 5271. lb/hr NOx emission rate 63.5 lb/hr HC emission rate 0.210 lb/hr CO emission rate 12.0 lb/hr L/D ratio 16.92 Total aircraft drag 5243. lbf. Segment 4 ends at total time = 22.2 mins, endmass = 88261.lb.(1.60g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +6960. +381. +48.49 +475.4 +5.19 +0.023 +1.43 Final : 41000. 1331. 142.89 2478.8 36.89 0.078 4.20 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 34040. 949.2 94.40 2003.4 4061. 277. 0.797 1656. 5243. 461. 34406. 962.6 96.11 2022.8 4023. 274. 0.797 1631. 5207. 461. 34772. 976.2 97.85 2042.4 3986. 272. 0.797 1606. 5172. 460. 35139. 990.0 99.61 2062.1 3941. 270. 0.797 1572. 5138. 459. 35505. 1004. 101.42 2082.0 3884. 268. 0.797 1523. 5105. 458. 35871. 1019. 103.29 2102.2 3827. 265. 0.797 1474. 5074. 458. 36238. 1035. 105.31 2123.7 3770. 263. 0.797 1304. 5044. 457. 36604. 1052. 107.48 2146.6 3714. 261. 0.797 1260. 5017. 457. 36970. 1070. 109.74 2170.0 3657. 259. 0.797 1214. 4991. 457. 37337. 1088. 112.09 2193.9 3600. 257. 0.797 1168. 4966. 457. 37703. 1107. 114.52 2218.3 3543. 254. 0.797 1122. 4942. 457. 38069. 1127. 117.07 2243.4 3486. 252. 0.797 1074. 4919. 457. 38436. 1148. 119.73 2269.3 3430. 250. 0.797 1026. 4898. 457. 38802. 1170. 122.51 2295.9 3373. 248. 0.797 978. 4878. 457. 39168. 1193. 125.44 2323.4 3316. 246. 0.797 929. 4858. 457. 39535. 1218. 128.53 2351.9 3259. 244. 0.797 879. 4840. 457. 39901. 1243. 131.81 2381.6 3203. 242. 0.797 829. 4824. 457. 40267. 1271. 135.28 2412.6 3150. 240. 0.797 781. 4808. 457. 40634. 1300. 138.96 2444.9 3098. 238. 0.797 735. 4794. 457. 41000. 1331. 142.89 2478.8 3046. 236. 0.797 688. 4781. 457. ----------------------------------------------------------------------------- Acceleration to 237.kts in level flight at 41000.feet =0.02g: Time +4.1 sec, Dist +0.53 n.miles, Fuelburn +5.0 lb. NOx +0.06 lb., HC +0.000 lb., CO +0.011 lb. ----------------------------------------------------------------------------- Manoeuvre segment 5 starts at: Initial Mass 88256. lb. (CL 0.46 trapezoidal) Initial Altitude 41000. feet (1.59g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 237. kts (input Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 2400. lbf. (level cruise) =86.4%MCR Climb/Descent rate 0. feet/min Flightpath angle 0.0 deg. (grad.0.00%) True airspeed 459. kts Fuel Flow rate 3077. lb/hr NOx emission rate 26.1 lb/hr HC emission rate 0.236 lb/hr CO emission rate 18.8 lb/hr L/D ratio 18.39 Total aircraft drag 4799. lbf. Segment 5 ends at total time = 146.2 mins, endmass = 82059.lb.(1.71g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +0. +7439. +948.22 +6196.7 +51.71 +0.488 +39.38 Final : 41000. 8774. 1091.63 8680.5 88.66 0.566 43.59 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 41000. 1335. 143.41 2483.8 2400. 237. 0.800 0. 4799. 459. 41000. 1717. 192.11 2809.9 2393. 237. 0.800 0. 4786. 459. 41000. 2100. 240.95 3136.1 2386. 237. 0.800 0. 4772. 459. 41000. 2484. 289.92 3462.2 2379. 237. 0.800 0. 4758. 459. 41000. 2869. 339.02 3788.3 2372. 237. 0.800 0. 4745. 459. 41000. 3256. 388.25 4114.5 2366. 237. 0.800 0. 4731. 459. 41000. 3643. 437.62 4440.6 2359. 237. 0.800 0. 4718. 459. 41000. 4031. 487.12 4766.8 2352. 237. 0.800 0. 4704. 459. 41000. 4421. 536.76 5092.9 2345. 237. 0.800 0. 4691. 459. 41000. 4811. 586.53 5419.1 2339. 237. 0.800 0. 4678. 459. 41000. 5203. 636.43 5745.2 2332. 237. 0.800 0. 4664. 459. 41000. 5595. 686.47 6071.3 2326. 237. 0.800 0. 4651. 459. 41000. 5989. 736.64 6397.5 2319. 237. 0.800 0. 4638. 459. 41000. 6384. 786.95 6723.6 2312. 237. 0.800 0. 4625. 459. 41000. 6779. 837.39 7049.8 2306. 237. 0.800 0. 4612. 459. 41000. 7176. 887.97 7375.9 2299. 237. 0.800 0. 4599. 459. 41000. 7574. 938.68 7702.1 2293. 237. 0.800 0. 4586. 459. 41000. 7973. 989.53 8028.2 2287. 237. 0.800 0. 4573. 459. 41000. 8373. 1040.51 8354.3 2280. 237. 0.800 0. 4560. 459. 41000. 8774. 1091.63 8680.5 2274. 237. 0.800 0. 4548. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 6 starts at: Initial Mass 82059. lb. (CL 0.43 trapezoidal) Initial Altitude 41000. feet (1.71g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 237. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 3045. lbf. (100% MCL) Climb/Descent rate 873. feet/min Flightpath angle 1.1 deg. (grad.1.88%) True airspeed 459. kts Fuel Flow rate 3917. lb/hr NOx emission rate 39.8 lb/hr HC emission rate 0.219 lb/hr CO emission rate 13.4 lb/hr L/D ratio 18.04 Total aircraft drag 4548. lbf. Segment 6 ends at total time = 153.6 mins, endmass = 81633.lb.(1.42g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +4000. +439. +55.98 +426.0 +4.08 +0.027 +1.66 Final : 45000. 9213. 1147.62 9106.4 92.74 0.593 45.25 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 41000. 8774. 1091.63 8680.5 3045. 237. 0.800 873. 4548. 459. 41211. 8789. 1093.51 8696.4 3015. 235. 0.800 845. 4538. 459. 41421. 8804. 1095.44 8712.7 2986. 234. 0.800 817. 4528. 459. 41632. 8820. 1097.45 8729.4 2956. 233. 0.800 789. 4519. 459. 41842. 8836. 1099.53 8746.5 2926. 232. 0.800 761. 4510. 459. 42053. 8853. 1101.69 8764.1 2897. 231. 0.800 732. 4502. 459. 42263. 8871. 1103.93 8782.3 2867. 230. 0.800 703. 4494. 459. 42474. 8889. 1106.27 8801.0 2837. 229. 0.800 674. 4487. 459. 42684. 8908. 1108.72 8820.3 2808. 228. 0.800 644. 4480. 459. 42895. 8928. 1111.28 8840.4 2778. 226. 0.800 615. 4473. 459. 43105. 8949. 1113.96 8861.2 2748. 225. 0.800 585. 4467. 459. 43316. 8971. 1116.79 8882.9 2719. 224. 0.800 554. 4461. 459. 43526. 8995. 1119.78 8905.5 2689. 223. 0.800 524. 4455. 459. 43737. 9020. 1122.95 8929.2 2659. 222. 0.800 493. 4450. 459. 43947. 9046. 1126.32 8954.2 2630. 221. 0.800 463. 4445. 459. 44158. 9074. 1129.93 8980.7 2600. 220. 0.800 431. 4441. 459. 44368. 9105. 1133.80 9008.8 2571. 219. 0.800 400. 4437. 459. 44579. 9138. 1138.00 9038.8 2541. 218. 0.800 368. 4434. 459. 44789. 9174. 1142.58 9071.2 2511. 217. 0.800 337. 4431. 459. 45000. 9213. 1147.62 9106.4 2482. 216. 0.800 304. 4428. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 7 starts at: Initial Mass 81633. lb. (CL 0.52 trapezoidal) Initial Altitude 45000. feet (1.42g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 216. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 2214. lbf. (level cruise) =97.5%MCR Climb/Descent rate 0. feet/min Flightpath angle 0.0 deg. (grad.0.00%) True airspeed 459. kts Fuel Flow rate 2841. lb/hr NOx emission rate 23.6 lb/hr HC emission rate 0.234 lb/hr CO emission rate 17.1 lb/hr L/D ratio 18.44 Total aircraft drag 4428. lbf. Segment 7 ends at total time = 504.5 mins, endmass = 66349.lb.(1.75g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +0. +21056. +2683.90 +15283.4 +119.95 +1.383 +107.83 Final : 45000. 30269. 3831.51 24389.9 212.69 1.976 153.08 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 45000. 9213. 1147.62 9106.4 2214. 216. 0.800 0. 4428. 459. 45000. 10237. 1278.13 9910.8 2194. 216. 0.800 0. 4389. 459. 45000. 11270. 1409.83 10715.2 2175. 216. 0.800 0. 4350. 459. 45000. 12313. 1542.72 11519.6 2156. 216. 0.800 0. 4312. 459. 45000. 13365. 1676.81 12324.0 2137. 216. 0.800 0. 4274. 459. 45000. 14426. 1812.10 13128.4 2119. 216. 0.800 0. 4237. 459. 45000. 15497. 1948.59 13932.8 2100. 216. 0.800 0. 4201. 459. 45000. 16577. 2086.29 14737.2 2082. 216. 0.800 0. 4165. 459. 45000. 17667. 2225.20 15541.6 2065. 216. 0.800 0. 4129. 459. 45000. 18767. 2365.34 16346.0 2047. 216. 0.800 0. 4094. 459. 45000. 19876. 2506.70 17150.4 2030. 216. 0.800 0. 4059. 459. 45000. 20994. 2649.26 17954.8 2013. 216. 0.800 0. 4025. 459. 45000. 22122. 2792.98 18759.1 1996. 216. 0.800 0. 3991. 459. 45000. 23258. 2937.85 19563.5 1979. 216. 0.800 0. 3958. 459. 45000. 24404. 3083.88 20367.9 1963. 216. 0.800 0. 3925. 459. 45000. 25559. 3231.07 21172.3 1946. 216. 0.800 0. 3893. 459. 45000. 26723. 3379.42 21976.7 1930. 216. 0.800 0. 3860. 459. 45000. 27896. 3528.94 22781.1 1914. 216. 0.800 0. 3829. 459. 45000. 29078. 3679.64 23585.5 1899. 216. 0.800 0. 3797. 459. 45000. 30269. 3831.51 24389.9 1883. 216. 0.800 0. 3766. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 8 starts at: Initial Mass 66349. lb. (CL 0.42 trapezoidal) Initial Altitude 45000. feet (1.75g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 216. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 2482. lbf. (100% MCL) Climb/Descent rate 838. feet/min Flightpath angle 1.0 deg. (grad.1.80%) True airspeed 459. kts Fuel Flow rate 3191. lb/hr NOx emission rate 29.1 lb/hr HC emission rate 0.222 lb/hr CO emission rate 13.9 lb/hr L/D ratio 17.62 Total aircraft drag 3766. lbf. Segment 8 ends at total time = 511.9 mins, endmass = 65996.lb.(1.45g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +4000. +445. +56.66 +353.8 +3.06 +0.027 +1.71 Final : 49000. 30714. 3888.17 24743.7 215.74 2.003 154.79 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 45000. 30269. 3831.51 24389.9 2482. 216. 0.800 838. 3766. 459. 45211. 30285. 3833.46 24403.4 2459. 214. 0.800 813. 3757. 459. 45421. 30300. 3835.48 24417.2 2436. 213. 0.800 787. 3748. 459. 45632. 30317. 3837.56 24431.3 2413. 212. 0.800 761. 3740. 459. 45842. 30334. 3839.71 24445.8 2390. 211. 0.800 735. 3731. 459. 46053. 30351. 3841.95 24460.7 2367. 210. 0.800 708. 3723. 459. 46263. 30369. 3844.26 24476.0 2344. 209. 0.800 681. 3716. 459. 46474. 30388. 3846.67 24491.8 2321. 208. 0.800 655. 3708. 459. 46684. 30408. 3849.19 24508.0 2298. 207. 0.800 627. 3701. 459. 46895. 30429. 3851.81 24524.9 2275. 206. 0.800 600. 3695. 459. 47105. 30450. 3854.56 24542.3 2252. 205. 0.800 572. 3688. 459. 47316. 30473. 3857.45 24560.4 2229. 204. 0.800 545. 3682. 459. 47526. 30497. 3860.48 24579.3 2206. 203. 0.800 516. 3676. 459. 47737. 30522. 3863.69 24599.0 2183. 202. 0.800 488. 3671. 459. 47947. 30548. 3867.09 24619.7 2160. 201. 0.800 460. 3666. 459. 48158. 30577. 3870.71 24641.5 2137. 200. 0.800 431. 3661. 459. 48368. 30607. 3874.58 24664.6 2114. 199. 0.800 402. 3657. 459. 48579. 30640. 3878.75 24689.1 2091. 198. 0.800 373. 3653. 459. 48789. 30675. 3883.26 24715.4 2068. 197. 0.800 343. 3649. 459. 49000. 30714. 3888.17 24743.7 2045. 196. 0.800 313. 3645. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 9 starts at: Initial Mass 65996. lb. (CL 0.51 trapezoidal) Initial Altitude 49000. feet (1.45g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 196. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 1822. lbf. (level cruise) =97.9%MCR Climb/Descent rate 0. feet/min Flightpath angle 0.0 deg. (grad.0.00%) True airspeed 459. kts Fuel Flow rate 2339. lb/hr NOx emission rate 17.6 lb/hr HC emission rate 0.235 lb/hr CO emission rate 17.2 lb/hr L/D ratio 18.11 Total aircraft drag 3645. lbf. Segment 9 ends at total time = 684.6 mins, endmass = 59545.lb.(1.61g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +0. +10362. +1320.80 +6450.3 +47.03 +0.682 +51.72 Final : 49000. 41076. 5208.97 31193.9 262.77 2.685 206.51 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 49000. 30714. 3888.17 24743.7 1822. 196. 0.800 0. 3645. 459. 49000. 31238. 3954.94 25083.2 1814. 196. 0.800 0. 3629. 459. 49000. 31764. 4022.01 25422.7 1806. 196. 0.800 0. 3613. 459. 49000. 32292. 4089.38 25762.1 1798. 196. 0.800 0. 3597. 459. 49000. 32823. 4157.05 26101.6 1791. 196. 0.800 0. 3581. 459. 49000. 33357. 4225.03 26441.1 1783. 196. 0.800 0. 3565. 459. 49000. 33892. 4293.31 26780.6 1775. 196. 0.800 0. 3550. 459. 49000. 34430. 4361.90 27120.1 1767. 196. 0.800 0. 3534. 459. 49000. 34971. 4430.79 27459.6 1760. 196. 0.800 0. 3519. 459. 49000. 35514. 4499.99 27799.1 1752. 196. 0.800 0. 3504. 459. 49000. 36059. 4569.50 28138.6 1744. 196. 0.800 0. 3489. 459. 49000. 36607. 4639.31 28478.0 1737. 196. 0.800 0. 3474. 459. 49000. 37157. 4709.43 28817.5 1729. 196. 0.800 0. 3459. 459. 49000. 37709. 4779.86 29157.0 1722. 196. 0.800 0. 3444. 459. 49000. 38264. 4850.60 29496.5 1715. 196. 0.800 0. 3429. 459. 49000. 38822. 4921.65 29836.0 1707. 196. 0.800 0. 3415. 459. 49000. 39382. 4993.02 30175.5 1700. 196. 0.800 0. 3400. 459. 49000. 39944. 5064.69 30515.0 1693. 196. 0.800 0. 3386. 459. 49000. 40509. 5136.67 30854.5 1686. 196. 0.800 0. 3371. 459. 49000. 41076. 5208.97 31193.9 1679. 196. 0.800 0. 3357. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 10 starts at: Initial Mass 59545. lb. (CL 0.46 trapezoidal) Initial Altitude 49000. feet (1.61g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 196. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 2045. lbf. (100% MCL) Climb/Descent rate 572. feet/min Flightpath angle 0.7 deg. (grad.1.23%) True airspeed 459. kts Fuel Flow rate 2630. lb/hr NOx emission rate 21.7 lb/hr HC emission rate 0.223 lb/hr CO emission rate 14.0 lb/hr L/D ratio 17.74 Total aircraft drag 3357. lbf. Segment 10 ends at total time = 689.4 mins, endmass = 59348.lb.(1.47g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +2000. +287. +36.52 +197.8 +1.58 +0.018 +1.13 Final : 51000. 41362. 5245.49 31391.7 264.36 2.703 207.64 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 49000. 41076. 5208.97 31193.9 2045. 196. 0.800 572. 3357. 459. 49105. 41087. 5210.40 31202.1 2034. 196. 0.800 557. 3354. 459. 49211. 41099. 5211.86 31210.4 2022. 195. 0.800 541. 3351. 459. 49316. 41110. 5213.37 31219.0 2011. 195. 0.800 526. 3348. 459. 49421. 41123. 5214.93 31227.7 1999. 194. 0.800 510. 3345. 459. 49526. 41135. 5216.53 31236.6 1988. 194. 0.800 495. 3342. 459. 49632. 41148. 5218.18 31245.8 1976. 193. 0.800 479. 3339. 459. 49737. 41162. 5219.89 31255.3 1965. 193. 0.800 463. 3337. 459. 49842. 41175. 5221.66 31265.0 1953. 192. 0.800 447. 3334. 459. 49947. 41190. 5223.50 31275.0 1942. 192. 0.800 431. 3331. 459. 50053. 41205. 5225.39 31285.3 1932. 191. 0.800 418. 3329. 459. 50158. 41220. 5227.35 31295.8 1923. 191. 0.800 406. 3326. 459. 50263. 41236. 5229.36 31306.7 1914. 191. 0.800 394. 3324. 459. 50368. 41252. 5231.44 31317.8 1905. 190. 0.800 382. 3322. 459. 50474. 41269. 5233.58 31329.2 1896. 190. 0.800 370. 3319. 459. 50579. 41286. 5235.80 31340.9 1887. 189. 0.800 357. 3317. 459. 50684. 41304. 5238.09 31353.0 1878. 189. 0.800 345. 3315. 459. 50789. 41323. 5240.47 31365.5 1869. 188. 0.800 333. 3313. 459. 50895. 41342. 5242.93 31378.4 1860. 188. 0.800 321. 3311. 459. 51000. 41362. 5245.49 31391.7 1852. 187. 0.800 308. 3309. 459. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 11 starts at: Initial Mass 59348. lb. (CL 0.50 trapezoidal) Initial Altitude 51000. feet (1.47g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 187. kts (fixed Mach 0.800) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 1655. lbf. (level cruise) =98.3%MCR Climb/Descent rate 0. feet/min Flightpath angle 0.0 deg. (grad.0.00%) True airspeed 459. kts Fuel Flow rate 2123. lb/hr NOx emission rate 15.2 lb/hr HC emission rate 0.236 lb/hr CO emission rate 17.2 lb/hr L/D ratio 17.93 Total aircraft drag 3309. lbf. Segment 11 ends at total time = 869.6 mins, endmass = 53242.lb.(1.63g buff) Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: +0. +10815. +1378.62 +6105.4 +42.33 +0.713 +54.17 Final : 51000. 52178. 6624.11 37497.1 306.69 3.416 261.81 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 51000. 41362. 5245.49 31391.7 1655. 187. 0.800 0. 3309. 459. 51000. 41908. 5315.10 31713.0 1647. 187. 0.800 0. 3294. 459. 51000. 42457. 5385.04 32034.4 1640. 187. 0.800 0. 3279. 459. 51000. 43008. 5455.30 32355.7 1632. 187. 0.800 0. 3265. 459. 51000. 43562. 5525.88 32677.1 1625. 187. 0.800 0. 3250. 459. 51000. 44118. 5596.79 32998.4 1618. 187. 0.800 0. 3235. 459. 51000. 44677. 5668.03 33319.7 1610. 187. 0.800 0. 3221. 459. 51000. 45239. 5739.59 33641.1 1603. 187. 0.800 0. 3206. 459. 51000. 45803. 5811.48 33962.4 1596. 187. 0.800 0. 3192. 459. 51000. 46369. 5883.70 34283.7 1589. 187. 0.800 0. 3178. 459. 51000. 46938. 5956.25 34605.1 1582. 187. 0.800 0. 3164. 459. 51000. 47510. 6029.13 34926.4 1575. 187. 0.800 0. 3150. 459. 51000. 48084. 6102.34 35247.7 1568. 187. 0.800 0. 3136. 459. 51000. 48661. 6175.88 35569.1 1561. 187. 0.800 0. 3122. 459. 51000. 49241. 6249.75 35890.4 1554. 187. 0.800 0. 3108. 459. 51000. 49823. 6323.95 36211.7 1547. 187. 0.800 0. 3095. 459. 51000. 50408. 6398.49 36533.1 1541. 187. 0.800 0. 3081. 459. 51000. 50995. 6473.36 36854.4 1534. 187. 0.800 0. 3068. 459. 51000. 51585. 6548.57 37175.7 1527. 187. 0.800 0. 3054. 459. 51000. 52178. 6624.11 37497.1 1521. 187. 0.800 0. 3041. 459. ----------------------------------------------------------------------------- Deceleration to 186.kts in level flight at 51000.feet =-0.04g: Time +2.3 sec, Dist +0.30 n.miles, Fuelburn +0.6 lb. NOx +0.00 lb., HC +0.000 lb., CO +0.016 lb. ----------------------------------------------------------------------------- Manoeuvre segment 12 starts at: Initial Mass 53242. lb. (CL 0.46 trapezoidal) Initial Altitude 51000. feet (1.64g buffet) Delta-ISA +0. deg.C Airspeed (CAS) 186. kts (input Mach 0.797) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 469. lbf. (idle) Climb/Descent rate -1818. feet/min Flightpath angle -2.2 deg. (grad.-3.93%) True airspeed 457. kts Fuel Flow rate 904. lb/hr NOx emission rate 3.9 lb/hr HC emission rate 0.546 lb/hr CO emission rate 24.5 lb/hr L/D ratio 17.58 Total aircraft drag 3028. lbf. Segment 12 ends at total time = 876.9 mins, endmass = 53135.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: -16960. +432. +54.85 +106.2 +0.44 +0.166 +4.72 Final : 34040. 52612. 6679.26 37603.9 307.13 3.582 266.54 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 51000. 52180. 6624.41 37497.7 469. 186. 0.797 -1818. 3028. 457. 50107. 52209. 6628.13 37505.0 469. 190. 0.797 -1840. 3054. 457. 49215. 52238. 6631.79 37512.3 469. 194. 0.797 -1867. 3084. 457. 48322. 52267. 6635.41 37519.4 469. 199. 0.797 -1898. 3119. 457. 47429. 52295. 6638.96 37526.5 469. 203. 0.797 -1933. 3159. 457. 46537. 52322. 6642.44 37533.3 469. 207. 0.797 -1971. 3203. 457. 45644. 52349. 6645.86 37540.1 469. 211. 0.797 -2014. 3252. 457. 44752. 52375. 6649.19 37546.7 463. 216. 0.797 -2070. 3305. 457. 43859. 52401. 6652.41 37553.0 444. 220. 0.797 -2157. 3365. 457. 42966. 52425. 6655.50 37559.1 424. 225. 0.797 -2248. 3431. 457. 42074. 52448. 6658.46 37564.8 405. 230. 0.797 -2343. 3501. 457. 41181. 52471. 6661.31 37570.4 386. 235. 0.797 -2443. 3576. 457. 40288. 52492. 6664.03 37575.6 366. 240. 0.797 -2547. 3657. 457. 39396. 52513. 6666.64 37580.6 332. 245. 0.797 -2681. 3742. 457. 38503. 52532. 6669.11 37585.3 291. 250. 0.797 -2831. 3833. 457. 37610. 52550. 6671.45 37589.6 250. 255. 0.797 -2987. 3929. 457. 36718. 52568. 6673.67 37593.8 209. 260. 0.797 -3147. 4030. 457. 35825. 52584. 6675.69 37597.5 168. 266. 0.797 -3624. 4139. 458. 34932. 52598. 6677.52 37600.8 127. 271. 0.797 -3830. 4257. 460. 34040. 52612. 6679.26 37603.9 86. 277. 0.797 -4043. 4380. 461. ----------------------------------------------------------------------------- ----------------------------------------------------------------------------- Manoeuvre segment 13 starts at: Initial Mass 53135. lb. (CL 0.20 trapezoidal) Initial Altitude 34040. feet Delta-ISA +0. deg.C Airspeed (CAS) 277. kts (input) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine 86. lbf. (idle) Climb/Descent rate -2845. feet/min Flightpath angle -3.5 deg. (grad.-6.09%) True airspeed 461. kts Fuel Flow rate 819. lb/hr NOx emission rate 3.2 lb/hr HC emission rate 1.578 lb/hr CO emission rate 40.2 lb/hr L/D ratio 12.13 Total aircraft drag 4380. lbf. Segment 13 ends at total time = 885.0 mins, endmass = 53035.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: -24040. +489. +52.26 +100.2 +0.38 +0.182 +4.56 Final : 10000. 53100. 6731.51 37704.1 307.52 3.764 271.10 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 34040. 52612. 6679.26 37603.9 86. 277. 0.797 -2845. 4380. 461. 32775. 52638. 6682.64 37609.9 41. 277. 0.777 -2856. 4352. 452. 31509. 52665. 6685.93 37615.8 -3. 277. 0.757 -2887. 4353. 443. 30244. 52691. 6689.11 37621.5 -49. 277. 0.738 -2925. 4367. 434. 28979. 52717. 6692.20 37627.1 -78. 277. 0.719 -2943. 4384. 426. 27714. 52743. 6695.21 37632.6 -110. 277. 0.701 -2962. 4401. 417. 26448. 52768. 6698.15 37638.0 -138. 277. 0.684 -2976. 4419. 409. 25183. 52794. 6701.02 37643.2 -164. 277. 0.667 -2985. 4436. 401. 23918. 52819. 6703.82 37648.4 -190. 277. 0.651 -2991. 4452. 393. 22653. 52844. 6706.57 37653.5 -214. 277. 0.635 -2994. 4467. 386. 21387. 52870. 6709.26 37658.5 -237. 277. 0.619 -2995. 4481. 378. 20122. 52895. 6711.90 37663.5 -259. 277. 0.604 -2992. 4494. 371. 18857. 52920. 6714.49 37668.4 -287. 277. 0.590 -2995. 4506. 364. 17592. 52946. 6717.03 37673.2 -312. 277. 0.576 -2993. 4517. 357. 16326. 52971. 6719.52 37678.1 -333. 277. 0.562 -2985. 4527. 350. 15061. 52997. 6721.98 37683.1 -351. 277. 0.549 -2973. 4536. 344. 13796. 53022. 6724.40 37688.2 -365. 277. 0.536 -2956. 4545. 337. 12531. 53048. 6726.80 37693.3 -376. 277. 0.524 -2934. 4552. 331. 11265. 53074. 6729.17 37698.6 -385. 277. 0.512 -2908. 4560. 325. 10000. 53100. 6731.51 37704.1 -390. 277. 0.500 -2879. 4566. 319. ----------------------------------------------------------------------------- Deceleration to 250.kts in level flight at 10000.feet =-0.09g: Time +17.1 sec, Dist +1.44 n.miles, Fuelburn +3.6 lb. NOx +0.01 lb., HC +0.006 lb., CO +0.143 lb. ----------------------------------------------------------------------------- Manoeuvre segment 14 starts at: Initial Mass 53032. lb. (CL 0.22 trapezoidal) Initial Altitude 10000. feet Delta-ISA +0. deg.C Airspeed (CAS) 250. kts (input) Flaps 0 deg. (hi-speed) Undercarriage up All eng.operative Thrust per engine -298. lbf. (idle) Climb/Descent rate -2274. feet/min Flightpath angle -4.4 deg. (grad.-7.78%) True airspeed 289. kts Fuel Flow rate 774. lb/hr NOx emission rate 3.0 lb/hr HC emission rate 1.220 lb/hr CO emission rate 30.3 lb/hr L/D ratio 13.33 Total aircraft drag 3979. lbf. Segment 14 ends at total time = 889.2 mins, endmass = 52972.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: -8500. +236. +17.79 +59.5 +0.24 +0.084 +2.10 Final : 1500. 53354. 6750.75 37767.2 307.77 3.855 273.35 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 10000. 53117. 6732.96 37707.7 -298. 250. 0.452 -2274. 3979. 289. 9553. 53129. 6733.90 37710.3 -298. 250. 0.449 -2264. 3980. 287. 9105. 53141. 6734.85 37712.9 -299. 250. 0.445 -2253. 3981. 285. 8658. 53153. 6735.79 37715.6 -298. 250. 0.441 -2242. 3982. 283. 8211. 53165. 6736.73 37718.3 -298. 250. 0.438 -2230. 3982. 281. 7763. 53177. 6737.67 37721.1 -297. 250. 0.434 -2219. 3983. 279. 7316. 53189. 6738.61 37724.0 -296. 250. 0.431 -2207. 3984. 278. 6868. 53201. 6739.54 37726.9 -295. 250. 0.427 -2195. 3985. 276. 6421. 53214. 6740.48 37729.9 -294. 250. 0.424 -2183. 3985. 274. 5974. 53226. 6741.42 37732.9 -292. 250. 0.420 -2171. 3986. 272. 5526. 53238. 6742.35 37736.0 -290. 250. 0.417 -2158. 3986. 270. 5079. 53251. 6743.29 37739.2 -288. 250. 0.413 -2145. 3987. 269. 4632. 53264. 6744.22 37742.5 -286. 250. 0.410 -2132. 3987. 267. 4184. 53276. 6745.15 37745.8 -283. 250. 0.407 -2119. 3988. 265. 3737. 53289. 6746.09 37749.2 -281. 250. 0.404 -2106. 3988. 264. 3289. 53302. 6747.02 37752.6 -278. 250. 0.400 -2093. 3988. 262. 2842. 53314. 6747.95 37756.2 -275. 250. 0.397 -2080. 3989. 260. 2395. 53327. 6748.88 37759.8 -273. 250. 0.394 -2068. 3989. 259. 1947. 53340. 6749.82 37763.5 -271. 250. 0.391 -2056. 3989. 257. 1500. 53354. 6750.75 37767.2 -269. 250. 0.388 -2043. 3989. 255. ----------------------------------------------------------------------------- Deceleration to 109.kts in level flight at 1500.feet =-0.27g: Time +28.2 sec, Dist +1.29 n.miles, Fuelburn +8.7 lb. NOx +0.04 lb., HC +0.011 lb., CO +0.275 lb. ----------------------------------------------------------------------------- Manoeuvre segment 15 starts at: Initial Mass 52963. lb. (CL 1.15 trapezoidal) Initial Altitude 1500. feet Delta-ISA +0. deg.C Airspeed (CAS) 109. kts (Vapp) Flaps 35 deg. Undercarriage down All eng.operative Thrust per engine 2497. lbf. (match grad.) =22.3%MCL Climb/Descent rate -592. feet/min Flightpath angle -3.0 deg. (grad.-5.24%) True airspeed 112. kts Fuel Flow rate 3560. lb/hr NOx emission rate 28.6 lb/hr HC emission rate 0.178 lb/hr CO emission rate 16.8 lb/hr L/D ratio 6.78 Total aircraft drag 7812. lbf. Segment 15 ends at total time = 892.2 mins, endmass = 52814.lb. Altitude Time Distance Fuel Burn NOx HC CO feet sec n.miles lb. lb. lb. lb. Increm: -1450. +149. +0.00 +149.1 +1.20 +0.007 +0.70 Final : 50. 53530. 6752.04 37925.0 309.01 3.873 274.32 ----------------------------------------------------------------------------- History: Alt Time Dist Burnt FN/eng CAS Mach RoC Drag TAS 1500. 53382. 0.000 37775.9 2497. 109. 0.170 -592. 7812. 112. 1339. 53398. 0.000 37792.1 2496. 109. 0.169 -591. 7810. 111. 1178. 53414. 0.000 37808.4 2496. 109. 0.169 -589. 7808. 111. 1017. 53431. 0.000 37824.8 2495. 109. 0.168 -588. 7805. 111. 856. 53447. 0.000 37841.3 2495. 109. 0.168 -586. 7803. 111. 694. 53464. 0.000 37857.8 2494. 109. 0.167 -585. 7801. 110. 533. 53480. 0.000 37874.5 2494. 109. 0.167 -583. 7798. 110. 372. 53497. 0.000 37891.2 2493. 109. 0.166 -582. 7796. 110. 211. 53514. 0.000 37908.1 2492. 109. 0.166 -580. 7794. 109. 50. 53530. 0.000 37925.0 2492. 109. 0.165 -579. 7791. 109. ----------------------------------------------------------------------------- Summary of segments in the sequence: ----------------------------------------------- Seg. Speed mode Thrust mode Stop condition 1. v3 at-%mto to alt 1500. 2. specify-cas at-%mcl to alt 10000. 3. specify-cas at-%mcl to mach 0.80 4. same-mach at-%mcl to alt 41000. 5. specify-mach level-cruise to next stepup 6. same-mach at-%mcl to dalt ±4000. 7. same-mach level-cruise to next stepup 8. same-mach at-%mcl to dalt ±4000. 9. same-mach level-cruise to next stepup 10. same-mach at-%mcl to dalt ±2000. 11. same-mach level-cruise to mass 53242. 12. specify-mach at-idle to cas 277. 13. specify-cas at-idle to alt 10000. 14. specify-cas at-idle to alt 1500. 15. vapp match-grad to alt 50. ----------------------------------------------- ?