Jsbsim Tutorial -
She opens the XML and says, “Good. But you forgot Reynolds number effects on your lift curve – it’s a small wing. And your propeller efficiency table is for sea level only. Add <function> inside propeller definition to scale with density.”
<aerodynamics> <axis name="LIFT"> <coefficient name="CL"> <function> <table> <independentVar lookup="row">aero/alpha-rad</independentVar> <independentVar lookup="column">fcs/camber-command</independentVar> <!-- data from wind tunnel: rows alpha (-0.2 to 0.4 rad), cols camber (0 to 0.05) --> <tableData> -0.2 -0.4 -0.35 ... 0.0 0.2 0.25 ... 0.4 1.2 1.3 ... </tableData> </table> </function> </coefficient> </axis> </aerodynamics> He does the same for drag and pitch moment. For sideforce, yaw, roll, he uses simpler stability derivatives.
Alex opens the drive. Inside: x1_fdm.xml , a blank JSBSim configuration file. No UI. Just XML. jsbsim tutorial
import jsbsim fdm = jsbsim.FGFDMExec() fdm.load_model('x1') fdm['propulsion/engine[0]/running'] = 1 fdm['fcs/throttle-cmd-norm'] = 1.0 for t in range(1000): fdm.Run() if t == 200: fdm['fcs/elevator-cmd-norm'] = -0.3 # pitch up print(fdm['position/h-sl-ft'], fdm['attitude/theta-deg'])
<metrics unit="KG" unit_area="M2" unit_length="M"> <wingarea> 12.0 </wingarea> <wingspan> 10.0 </wingspan> <chord> 1.2 </chord> </metrics> All units are SI internally, but you can specify units per value. JSBSim converts. Part 3: The Aerodynamics Puzzle – Coefficient Tables Now the hardest part: the X‑1 has a variable‑camber wing (no flaps, but morphing trailing edge). No existing table works. She opens the XML and says, “Good
The first section: <?xml version="1.0"?> followed by <fdm_config> .
Maya hands Alex wind tunnel data: CL(alpha, camber) , CD(alpha) , Cm(alpha) . followed by <
JSBSim outputs time‑step data to x1_taxi.csv . Alex plots yaw vs time. Works perfectly – the aircraft turns, gear compresses, no oscillation.