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R1517/data/umx_radian.yaml
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umx_radian.yaml
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name: umx_radian
geometry:
b: 0.730 # wing span [m]
c: 0.076 # mean aerodynamic chord (MAC)[m]
AR: 9.911 # aspect ratio []
S: 0.054 # wing surface area [m2]
lam: 2.050 # taper ratio []
St: 0.0085 # horizontal tail surface area [m2]
lt: 0.242 # tail level arm [m]
Sf: 0.0043 # fin surface area [m2]
lf: 0.242 # fin level arm [m]
Xac: 0.25 # aerodynamic centre [1/c]
inertia:
mass: 0.044 # [kg]
Ixx: 0.0003456 # [kg * m2]
Iyy: 0.000337 # [kg * m2]
Izz: 0.0006623 # (0.0006623)[kg * m2]
Ixz: -3.5e-5 # [kg * m2]
aerodynamic:
CL0: 0.119 # 0.219 lift coefficient with zero angle of attack (AoA) [] = CL0_wing
CL0_tail: 0.0 # horizontal tail zero AoA lift coefficient []
CLa_total: 4.483 # 5.483 total lift coefficient derivative with respect to AoA [1/rad]
CLa_wing: 5.317 # lift coefficient sensitivity of a wing wrt AoA [1/rad]
CLa_tail: 4.9656 # tail lift coefficient sensitivity wrt AoA [1/rad]
e_oswald: 0.82 # Oswald efficiency number []
CD0_total: 0.023 # (0.018)total zero lift drag coefficient []
CD0_wing: 0.015 # wing zero lift drag coefficient []
CD0_tail: 0.013 # tail zero lift drag coefficient []
CYb: -0.11351 # total side force coefficient [1/rad] (in BRF !!!)
CYb_vtail: 4.9656 # fin only side force coefficient []
Cm0: 0.005 # (5e-3) zero AoA pitching moment
Cma: -0.4118 # (-0.4118) pitching moment coefficient sensitivity wrt to AoA [1/rad]
Cn0: 0.0 # zero yawing moment for symmetric aircrafts []
Cnb: 0.0248 # (0.0248)yawing moment sensitivity wrt to sideslip [1/rad]
Cl0: 0.0 # rolling moment for symmetric aircrafts
Clb: -0.08389 # (-0.08389) rolling moment sensitivity wrt to sideslip angle [1/rad]
CLq: 7.169 # pitch-rate lift coefficient [1/rad] // Etkin and Stengel give different estimation !!!
Cmq: -12.665 # (Cmq = -12.665) pitch-rate moment coefficient [1/tad] //Etkin and Stengel give different estimation !!!
CYr: 0.085113 # yaw-rate side force effect [] //Etkin gives CYr = CLa_t * (Sf/S) * 2 * (lf/b)
Cnr: -0.0228 # (-0.1) yaw-rate yawing moment effect [] //Etkin gives Cnr = -CLa_t * Vf * (2*lf/b)
Clr: 0.0686 # (0.0686) yaw-rate rolling moment effect []
CYp: -0.1451 # roll-rate side force coefficient []
Clp: -0.5634 # roll-rate rolling moment coefficient [] //Stengel gives Clp = - (CLa_w / 12) * ((1 + 3*lam)/(1+lam))
Cnp: -0.03674 # roll-rate yawing moment coefficient []
CLde: 0.45 # lift sensitivity to elevator deflection [1/rad] (CZde = -0.45)
CYdr: 0.13208 # side force sensitivity to rudder deflection [1/rad] (~ not consistent 0.13208)
Cmde: -1.3132 # pitch moment sensitivity wrt to elevator deflection [1/rad]
Cndr: -0.03743 # yawing moment sensitivity wrt to rudder deflection [1/rad]
Cldr: 0.0055 # (0.0055)rolling moment sensitivity wrt to rudder deflection
CDde: -0.0037 # drag force sensitivity wrt elevator deflection
tether:
length: 2.81 # tether length
Ks: 0.66 # spring coefficient
Kd: 0.44 # damping coefficient
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