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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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Source: * Richard Murray's F16 Model page, NASA TP-1538 wind tunnel data. (Dec. 1979) http://www.cds.caltech.edu/~murray/projects/afosr95-vehicles/models/f16/ * "Observers Aircraft" by William Green, 1987 Edition (ISBN 0-7232-3458-2) * General Dynamics F-16 Dash-1 (basic drag and weight data only) * Modern Air Combat by Bill Gunston and Mike Speck, 1983 (ISBN 0-86101-1627) Drag due to Poly Tanks: CD: AOA Clean Tanks ----- ----- ----- 0.0000 0.119 0.407 0.4538 0.109 0.247 Wing profiles configuration LEF TEF ------------- --- --- Take-off, wow -2 20 Take-off, no wow 15 20 High speed course -2 -2 Max manoeuvre 25 0 Approach, no wow 15 20 Landing, wow -2 20 General Dynamics F-16A Block 15(+) Geometric characteristics and performance data Max speed: Mach 2.05 at 39,000 Ft Ceiling: 60,000 Ft Climb speed: 1033.5 Ft/Sec * Wing * Ventral Fin (Each) Area: 300 Sq Ft Area: 8.03 Sq Ft Wetted Area: 341.1 Sq Ft Wetted Area: 15.3 Sq Ft Span: 30 Ft 0 In Exposed Span: 27.5 In Reff. Lenght: 47 Ft 6.24 In Reff. Lenght: 23.356 In Aspect Ratio: 3.0 Aspect Ratio: 0.472 (Theo) Taper Ratio: 0.2275 Taper Ratio: 0.760 (Theo) Mean Chord: 11.32 Ft Mean Chord: 4.15 In Sweep(LE) 40 Degr Sweep(LE): 30 Degr Dihedral: 0 Degr Dihedral (Cant): 15 Degr Outbound Airfoil: NACA 64A204 Airfoil Incidence: 0 Degr at Root: 3.886% Modified Wedge Twist: at Tip: Constant 0.03R at SS 54.0: 0 Degr at SS 180.0: 3 Degr * Speed Brake Flaperon Area: 31.32 Sq Ft Area: 14.26 Sq Ft (3.565 Sq Ft Ea) LEF Area: 36.71 Sq Ft (4 Element Clamshell) * Horizontal Tail (Movable) * Landing Gear Area: 63.70 Sq Ft Main Gear (MLG) Wetted Area: 127.8 Sq Ft Tire Size: 25.5*8-14 (18 Ply) Semi Span: 5.80 Ft Stroke: 10.5 In Reff. Lenght: 5.90 Ft Static Rolling Radius: 11.0 In Aspect Ratio: 1.33 Taper Ratio: 0.390 (Theo) Nose Gear (NLG) Mean chord: 4.725 In Tire Size: 18*5.5-8 (18 Ply) Sweep(LE): 40 Degr Stroke: 10.0 In Dihedral: -10 Degr Static Rolling Radius: 7.5 In Airfoil at Root: 6% Biconvex * Propulsion at Tip: 3.5 Biconvex Engine: F-100-PW-200/220 Trhust: 25,000 Lb Class * Vertical Tail Engine Compressor Area: 54.75 Sq Ft Face Dia: 34.8 In Wetted Area: 128.7 Sq Ft Engine Length: 191.16 In Exposed Span: 2.30 Ft Reff. Length: 6.84 Ft * Fuselage Aspect Ratio: 1.62 Wetted Area: 775.8 Sq Ft Taper Ratio: 0.437 Inlet Area: 5.74 Sq Ft Mean Chord: 5.47 In Exit Area: 4.32 Sq Ft Sweep(LE): 47.5 Degr Chamber Area: 5.07 Sq Ft Airfoil Lenght: 49 Ft 5.9 In at Root: 5.3% Biconvex Reff. Length: 47.52 Ft at Tip: 3.0% Bicobvex Height: 16 Ft 8.5 In Rudder Area: 11.65 Sq Ft Aircraft refference locations (realtive to the centerpoint at the front of the nozzle): X Y Z ------ --------- ------ Center of Garvity 201.3 0.0 0.0 Pilot's eyepoint 384.7 0.0 33.2 Radome tip 525.0 0.0 -13.0 Top vertical tail 0.0 0.0 127.5 Wingtip 128.0 +/-197.0 0.0 Nose landing gear 332.2 0.0 -73.0 Main landing gear 171.9 +/-46.7 -73.0 Ventral fin 111.1 +/-24.0 -51.3 Air intake 350.7 0.0 -41.0 Fueltank 171.3 +/-71.5 0.0