File: albtros1.des


Effective_Stab_Area_(in^2)................ 0
Stab_Aerodynamic_Center_(AC)_coordinate... 26
Effective_Fin_Area_(in^2)................. 30
Fin_AC_coordinate......................... 26
Inside_wing_panel_1_root_LE_coordinate.... 0
Inside_wing_panel_1_root_TE_coordinate.... 7
Inside_wing_panel_1_span.................. 32
Inside_wing_panel_1_dihedral_angle_1...... 3
Inside_wing_panel_1_tip_LE_coordinate..... 2
Inside_wing_panel_1_tip_TE_coordinate..... 7
Next_wing_panel_2_span.................... 0
Next_wing_panel_2_dihedral_angle_2........ 0
Next_wing_panel_2_tip_LE_coordinate....... 0
Next_wing_panel_2_tip_TE_coordinate....... 0
Next_wing_panel_3_span.................... 0
Next_wing_panel_3_dihedral_angle_3........ 0
Next_wing_panel_3_tip_LE_coordinate....... 0
Next_wing_panel_3_tip_TE_coordinate....... 0
Next_wing_panel_4_span.................... 0
Next_wing_panel_4_dihedral_angle_3........ 0
Next_wing_panel_4_tip_LE_coordinate....... 0
Next_wing_panel_4_tip_TE_coordinate....... 0
Next_wing_panel_5_span.................... 0
Next_wing_panel_5_dihedral_angle_3........ 0
Next_wing_panel_5_tip_LE_coordinate....... 0
Next_wing_panel_5_tip_TE_coordinate....... 0



File:  albtros1.des

Design Analysis Results:


W_Area =  383.602 = Projected Wing Area (=2.664ft^2)
W_Span =   63.912 = Projected Wing Span
Cavg   =    6.002 = Average Wing Chord
AR     =   10.649 = Wing Aspect Ratio
C_Mom  =    0.970 = Datum to Leading Edge of Cavg
P_Mom  =   23.229 = 30% Cavg to Stab AC
Y_Mom  =   23.229 = 30% Cavg to Fin AC
Psf    =    0.000 = Pitch Stability Factor (0.45 preferred)
Ysf    =    0.028 = Yaw Stability Factor        
                    (0.017 for polydih. wing, 0.023 for aileron wing)
Rmf    =    0.052 = Yaw to Roll Coupling Factor 
                    (0.200 for polydih. wing, 0.052 for aileron wing)