diff --git a/data/umx_radian.yaml b/data/umx_radian.yaml
new file mode 100644
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+++ b/data/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