<?xml version="1.0"?> <turbine_engine name="V2527_A5"> <milthrust> 26600 </milthrust> <!-- Will put proper thrust amount once FDE sorted out --> <bypassratio> 10.1 </bypassratio> <tsfc> 0.5 </tsfc> <bleed> 0.03 </bleed> <idlen1> 22.4 </idlen1> <idlen2> 60.9 </idlen2> <n1spinup> 0.2 </n1spinup> <n2spinup> 2.0 </n2spinup> <maxn1> 105.8 </maxn1> <maxn2> 102.1 </maxn2> <augmented> 0 </augmented> <injected> 0 </injected> <function name="IdleThrust"> <table> <independentVar lookup="row">velocities/mach</independentVar> <independentVar lookup="column">atmosphere/density-altitude</independentVar> <tableData> -10000 0 10000 20000 30000 40000 50000 0.0 0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.1467 0.2 0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342 0.4 0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203 0.6 0.0 0.0 0.0 0.0 0.0276 0.0718 0.1073 0.8 0.0 0.0 0.0 0.0 0.0474 0.0868 0.0900 1.0 0.0 0.0 0.0 0.0 0.0 0.0552 0.0800 </tableData> </table> </function> <function name="MilThrust"> <table> <independentVar lookup="row">velocities/mach</independentVar> <independentVar lookup="column">atmosphere/density-altitude</independentVar> <tableData> -10000 0 10000 20000 30000 40000 50000 0.0 1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490 0.2 1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430 0.4 1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450 0.6 1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540 0.8 1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1600 0.9 1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.0000 1.0 1.1810 0.9510 0.7210 0.5320 0.3780 0.0000 0.0000 1.2 1.1500 0.9210 0.6920 0.0000 0.0000 0.0000 0.0000 1.4 1.1710 0.9340 0.0000 0.0000 0.0000 0.0000 0.0000 </tableData> </table> </function> </turbine_engine>