File: da_templ.des


Effective_Stab_Area_(in^2)................ 86
Stab_Aerodynamic_Center_(AC)_coordinate... 30
Effective_Fin_Area_(in^2)................. 55
Fin_AC_coordinate......................... 35
Inside_wing_panel_1_root_LE_coordinate.... 0
Inside_wing_panel_1_root_TE_coordinate.... 9
Inside_wing_panel_1_span.................. 26
Inside_wing_panel_1_dihedral_angle_1...... 6.6
Inside_wing_panel_1_tip_LE_coordinate..... 1
Inside_wing_panel_1_tip_TE_coordinate..... 9
Next_wing_panel_2_span.................... 24
Next_wing_panel_2_dihedral_angle_2........ 8
Next_wing_panel_2_tip_LE_coordinate....... 4
Next_wing_panel_2_tip_TE_coordinate....... 9
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:  da_templ.des

Design Analysis Results:


W_Area =  741.187 = Projected Wing Area
W_Span =   98.105 = Projected Wing Span
Cavg   =    7.555 = Average Wing Chord
AR     =   12.985 = Wing Aspect Ratio
C_Mom  =    1.353 = Datum to Leading Edge of Cavg
P_Mom  =   26.381 = 30% Cavg to Stab AC
Y_Mom  =   31.381 = 30% Cavg to Fin AC
Psf    =    0.405 = Pitch Stability Factor (0.4 preferrred)
Ysf    =    0.024 = Yaw Stability Factor        
                    (0.020 for polydih. wing, 0.030 for aileron wing)
Rmf    =    0.201 = Yaw to Roll Coupling Factor 
                    (0.20 for polydih. wing, 0.052 for aileron wing)
Pdf    =    1.022 = Pitch Damping Factor ( 1.000 preferred)