File: albtros2.des


Effective_Stab_Area_(in^2)................ 0
Stab_Aerodynamic_Center_(AC)_coordinate... 33
Effective_Fin_Area_(in^2)................. 54
Fin_AC_coordinate......................... 33
Inside_wing_panel_1_root_LE_coordinate.... 0
Inside_wing_panel_1_root_TE_coordinate.... 9
Inside_wing_panel_1_span.................. 47
Inside_wing_panel_1_dihedral_angle_1...... 0
Inside_wing_panel_1_tip_LE_coordinate..... .75
Inside_wing_panel_1_tip_TE_coordinate..... 7.75
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:  albtros2.des

Design Analysis Results:


W_Area =  752.188 = Projected Wing Area (=5.224ft^2)
W_Span =   94.000 = Projected Wing Span
Cavg   =    8.002 = Average Wing Chord
AR     =   11.747 = Wing Aspect Ratio
C_Mom  =    0.379 = Datum to Leading Edge of Cavg
P_Mom  =   30.220 = 30% Cavg to Stab AC
Y_Mom  =   30.220 = 30% Cavg to Fin AC
Psf    =    0.000 = Pitch Stability Factor (0.45 preferred)
Ysf    =    0.023 = Yaw Stability Factor        
                    (0.017 for polydih. wing, 0.023 for aileron wing)
Rmf    =    0.000 = Yaw to Roll Coupling Factor 
                    (0.200 for polydih. wing, 0.052 for aileron wing)