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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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Root Tip ------------ ----------- Fokker 100 Fokker 12.3% Fokker 9.6% Fokker 50 NACA 64-421 NACA 64-415 Fokker 60 NACA 64-421 NACA 64-415 Fokker 70 Fokker 12.3% Fokker 9.6% ------------------------------------------------------------------------------- http://rahauav.com/Library/Aerodynamic/Aerodynamic_design_of_transport_aircraft_www.rahaUAV.com.pdf Aerodynamic Design of Transport Aircraft Figure 27.14 Tail-Off lift curves for the Fokker 100 (Source: Fokker Rep. A-166 and A-173 alpha flaps (deg) (deg) 0 20 42 0.0 0.22 0.84 1.27 10.0 1.11 1.70 2.17 12.0 1.27 1.83 2.31 14.0 1.40 1.72 1.90 16.0 1.34 0.71 0.00 Figure 27.23 Drag due to flap deflection at three angles of attack, Fokker 100 (Source: Fokker Rep. A-166 and A-173) alpha flaps (deg) (deg) 0 20 42 -4.0 0.0000 0.0047 0.0156 0.0 0.0000 0.0070 0.0200 2.0 0.0001 0.0077 0.0225 4.0 0.0005 0.0089 0.0257 6.0 0.0008 0.0129 0.0276 8.0 0.0025 0.0156 0.0313 Figure 33.9 Comparison of aileron effectiveness from wind tunnel and flight tests - Fokker F-28 Mk 1000 (Source: Fokker report V-28-75) Clda flaps (deg) Mach 10 20 0.60 -0.022 -0.043 0.65 -0.022 -0.037 0.70 -0.023 -0.027 0.75 -0.019 -0.027 0.80 -0.015 -0.026 ------------------------------------------------------------------------------- Advanced Topics in Aerodynamics, Aerodynamic Database (AD) http://aerodyn.org/HighLift/tables.html --- CLmax 3.45 (in ground effect) ------------------------------------------------------------------------------- Butterworth-Heinemann - Civil Jet Aircraft Design http://booksite.elsevier.com/9780340741528/appendices/data-a/default.htm http://booksite.elsevier.com/9780340741528/appendices/data-a/table-8/table.htm --- CLmax (t/o) 2.17 (Df = 15 degrees) CLmax (l/d@MLM) 2.59 (Df = 42 degrees) ------------------------------------------------------------------------------- Lissys - Piano-X output: http://www.lissys.demon.co.uk/f7tx2.html (Note: Simulated Fokker 70 data) --- CLmax (t/o) 1.91 (Df = 0 degrees) L/D (2nd sgement) 12.54 (incl. windmill. & asymm). CLmax (l/d) 2.43 (Df = 42 degrees) L/D (approach) 4.91 (gear down) AERODYNAMIC DRAG REPORT (Altitude: 0ft) ------------------------------------------------------- MACH CD0 CDi CDmach CDtrim CDtotal| CL | SFC ----- ------- ------- ------- ------- -------|-----|------ 0.212 0.02035 0.05398 0.00190 -.00011 0.07613|1.099|0.7209 0.230 0.02013 0.04096 0.00000 0.00013 0.06122|0.957|0.7520 0.272 0.01957 0.01975 0.00000 0.00042 0.03975|0.665|0.8105 0.302 0.01925 0.01296 0.00000 0.00047 0.03268|0.539|0.8341 0.378 0.01857 0.00531 0.00000 0.00045 0.02432|0.345|0.8575 0.454 0.01801 0.00256 0.00000 0.00039 0.02096|0.239|0.8627 0.600 0.01712 0.00083 0.00000 0.00030 0.01826|0.137|0.8574 0.800 0.01614 0.00027 0.00373 0.00023 0.02036|0.077|0.8552 0.840 0.01596 0.00022 0.01067 0.00022 0.02707|0.070|0.8909 0.860 0.01587 0.00020 0.01858 0.00021 0.03487|0.067|0.8985 AERODYNAMIC DRAG REPORT (Altitude: 1000ft) ------------------------------------------------------- MACH CD0 CDi CDmach CDtrim CDtotal| CL | SFC ----- ------- ------- ------- ------- -------|-----|------ 0.653 0.01691 0.00064 0.00026 0.00028 0.01809|0.120|0.8476 0.771 0.01633 0.00033 0.00201 0.00024 0.01891|0.086|0.8524 0.800 0.01620 0.00028 0.00373 0.00023 0.02045|0.080|0.8516 AERODYNAMIC DRAG REPORT (Altitude: 35000ft) ------------------------------------------------------- MACH CD0 CDi CDmach CDtrim CDtotal| CL | SFC ----- ------- ------- ------- ------- -------|-----|------ 0.458 0.02102 0.04432 0.00222 0.00007 0.06763|0.996|0.5924 0.546 0.02034 0.02207 0.00017 0.00040 0.04299|0.703|0.6251 0.603 0.01995 0.01482 0.00036 0.00046 0.03560|0.576|0.6474 0.720 0.01922 0.00867 0.00115 0.00013 0.02917|0.440|0.6908 0.741 0.01910 0.00648 0.00152 0.00046 0.02756|0.381|0.6976 0.768 0.01894 0.00562 0.00251 0.00045 0.02752|0.355|0.7112 0.800 0.01876 0.00478 0.00541 0.00044 0.02939|0.327|0.7392 0.848 0.01855 0.00393 0.01616 0.00042 0.03906|0.296|0.7526 0.860 0.01844 0.00358 0.02737 0.00042 0.04981|0.283|0.7575 ------------------------------------------------------------------------------- Buffet envelope prediction of transport aircraft during the conceptual design phase - Predict transonic, shock induced buffet onset J.N.A. van Eijndhoven BSc Figure 4.2: Fokker 100 buffet onset flight test M CL 0.5 1.00 0.55 0.93 0.60 0.88 0.70 0.86 0.75 0.65 0.80 0.52 0.85 0.25 Table 1: dCL for literature and Matrix-V results, Fokker 100 wing, Λ0.5c at Re ≈ 1.5 · 107 M∞ CLLit [−] CLM atV [−] dCL [−] 0.65 0.86 0.83 0.03 0.68 0.86 0.84 0.02 0.70 0.87 0.85 0.02 0.73 0.72 0.81 -0.09 0.75 0.68 0.71 -0.03 Figure 3.2: Fuselage effect on wing lift distribution Body Ise Tip 0 0.5 0.75 1.0 CL 0.73 0.7 0.68 0.3