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jsbsim.js

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JSBSim flight dynamics model ported to JavaScript

github.com/csbrandt/JSBSim.js

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<?xml version="1.0"?> <!-- ZLT NT-07 airship flight model for JSBSim. Copyright (C) 2008 - 2010 Anders Gidenstam (anders(at)gidenstam.org) This file is licensed under the GPL license version 2 or later. --> <propeller name="Hoffman HO-V373()-D variable pitch"> <documentation> Data according to [FAA:2008:P30BO]: #blades 3 Weight 81.6 lb Diameter 2.70m Maximum continous/Take-off RPM 1250 HP 200 Blade twist limits (0.2 to 1.0 radius) 0 - 50 deg Pitch change rate: +35 to -25 deg Spinner weight 4.0 lb </documentation> <documentation> JavaProp: (Designed for Vne at max pitch. Other data generated by modifying pitch -10 and -15 deg.) #blades 3 n 1200 RPM D 2.70 m Spinner D 0.20 m Velocity 36.011111 m/s Power 134225.98 W Airfoil Clark Y, Re=500000 Clark Y, Re=500000 Clark Y, Re=500000 Flat plate, Re=500000 v/(nD) 0.667 v/(ΩR) 0.212 Efficiency η 73.427 % loading medium Thrust T 2,736.84 N Ct 0.1054 Power P 134.22 kW Cp 0.0958 β at 75%R 21.9° Pitch H 2.55 m </documentation> <documentation> The intertia is assumed to be n * 1/3*m_b*(d^2)/4 where n is the number of blades, m_b is the mass of a blade and d is the diameter. 2/3 of the total propeller weight is assumed to be in the blades. </documentation> <ixx> 33.168879 </ixx> <diameter unit="M"> 2.700 </diameter> <numblades> 3 </numblades> <gearratio> 2.16 </gearratio> <minpitch> -25 </minpitch> <maxpitch> 35 </maxpitch> <ct_factor> 1.00 </ct_factor> <cp_factor> 0.85 </cp_factor> <!-- Tweak --> <table name="C_THRUST" type="internal"> <!-- -0.00100 = NA --> <tableData> -25.0 -20.00 0.00 20.00 25.00 35.00 0.00000 -0.14081 -0.11035 -0.00100 0.11035 0.14081 0.16647 0.05000 -0.14738 -0.11248 -0.00100 0.11248 0.14738 0.15436 0.10000 -0.14444 -0.08987 -0.00100 0.08987 0.14444 0.17284 0.15000 -0.12447 -0.06553 -0.00100 0.06553 0.12447 0.17288 0.20000 -0.10031 -0.05007 -0.00100 0.05007 0.10031 0.16874 0.25000 -0.08937 -0.04022 -0.00100 0.04022 0.08937 0.16626 0.30000 -0.07940 -0.02937 -0.00100 0.02937 0.07940 0.16239 0.35000 -0.06841 -0.01752 -0.00100 0.01752 0.06841 0.15921 0.40000 -0.05648 -0.00483 -0.00100 0.00483 0.05648 0.15505 0.45000 -0.04372 -0.00100 -0.00100 -0.00848 0.04372 0.14971 0.50000 -0.03032 -0.00100 -0.00100 -0.02185 0.03032 0.14325 0.55000 -0.01629 -0.00100 -0.00100 -0.03522 0.01629 0.13459 0.60000 -0.00162 -0.00100 -0.00100 -0.04859 0.00162 0.12266 0.65000 -0.00100 -0.00100 -0.00100 -0.06196 -0.01336 0.10985 0.70000 -0.00100 -0.00100 -0.00100 -0.07533 -0.02834 0.09663 0.75000 -0.00100 -0.00100 -0.00100 -0.08870 -0.04332 0.08302 0.80000 -0.00100 -0.00100 -0.00100 -0.10207 -0.05830 0.06899 0.85000 -0.00100 -0.00100 -0.00100 -0.11544 -0.07328 0.05456 0.90000 -0.00100 -0.00100 -0.00100 -0.12881 -0.08826 0.03975 0.95000 -0.00100 -0.00100 -0.00100 -0.14218 -0.10324 0.02456 1.00000 -0.00100 -0.00100 -0.00100 -0.15555 -0.11822 0.00895 1.05000 -0.00100 -0.00100 -0.00100 -0.16892 -0.13320 -0.00708 1.10000 -0.00100 -0.00100 -0.00100 -0.18229 -0.14818 -0.02311 1.15000 -0.00100 -0.00100 -0.00100 -0.19566 -0.16316 -0.03913 1.20000 -0.00100 -0.00100 -0.00100 -0.20903 -0.17814 -0.05516 1.25000 -0.00100 -0.00100 -0.00100 -0.22240 -0.19312 -0.07118 1.30000 -0.00100 -0.00100 -0.00100 -0.23577 -0.20810 -0.08721 </tableData> </table> <table name="C_POWER" type="internal"> <!-- 0.00 = NA. 0 pitch is a guess. --> <tableData> -25.0 -20.00 0.00 20.00 25.00 35.00 0.00000 0.05405 0.03050 0.00560 0.03050 0.05405 0.13006 0.05000 0.04904 0.02772 0.00560 0.02772 0.04904 0.11229 0.10000 0.05310 0.02933 0.00560 0.02933 0.05310 0.12663 0.15000 0.05315 0.02731 0.00560 0.02731 0.05315 0.12920 0.20000 0.04981 0.02441 0.00560 0.02441 0.04981 0.12939 0.25000 0.04713 0.02204 0.00560 0.02204 0.04713 0.12312 0.30000 0.04410 0.01903 0.00560 0.01903 0.04410 0.12054 0.35000 0.04031 0.01528 0.00560 0.01528 0.04031 0.12003 0.40000 0.03568 0.01075 0.00560 0.01075 0.03568 0.11922 0.45000 0.03028 0.01000 0.00560 0.01000 0.03028 0.11789 0.50000 0.02405 0.01000 0.00560 0.01000 0.02405 0.11594 0.55000 0.01690 0.01000 0.00560 0.01000 0.01690 0.11245 0.60000 0.00875 0.01000 0.00560 0.01000 0.00875 0.10613 0.65000 0.01000 0.01000 0.00560 0.01000 0.01000 0.09854 0.70000 0.01000 0.01000 0.00560 0.01000 0.01000 0.08999 0.75000 0.01000 0.01000 0.00560 0.01000 0.01000 0.08045 0.80000 0.01000 0.01000 0.00560 0.01000 0.01000 0.06988 0.85000 0.01000 0.01000 0.00560 0.01000 0.01000 0.05824 0.90000 0.01000 0.01000 0.00560 0.01000 0.01000 0.04553 0.95000 0.01000 0.01000 0.00560 0.01000 0.01000 0.03177 1.00000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01691 1.05000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 1.10000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 1.15000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 1.20000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 1.25000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 1.30000 0.01000 0.01000 0.00560 0.01000 0.01000 0.01000 </tableData> </table> </propeller>