SuperGee 0.0 ! Mach 0 0 0.0 ! iYsym iZsym Zsym 336.0 5.5 59.0 ! Sref Cref Bref reference area, chord, span 3.00 0.0 0.5 ! Xref Yref Zref moment reference location (arb.) 0.020 ! CDp # #============================================================== # SURFACE Wing 10 1.0 22 1.0 ! Nchord Cspace Nspan Sspace # # reflect image wing about y=0 plane YDUPLICATE 0.00000 # # twist angle bias for whole surface ANGLE 2.00000 # SCALE 1.0 1.0 1.0 # # x,y,z bias for whole surface TRANSLATE 5.04000 0.00000 0.90000 # #-------------------------------------------------------------- # Xle Yle Zle chord angle Nspan Sspace SECTION -5.040 0.0 0.0 7.20 0.000 9 -0.75 AFIL ag45c.dat #Cname Cgain Xhinge HingeVec SgnDup CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 #----------------------------- SECTION -3.850 20.0 1.75 5.50 0.000 5 -1.25 AFIL ag46c.dat CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 #----------------------------- SECTION -2.716 27.2 2.380 3.88 0.000 3 -1.25 AFIL ag47c.dat CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 #----------------------------- SECTION -2.275 28.7 2.510 3.25 0.000 2 -1.25 AFIL ag47c.dat CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 #----------------------------- SECTION -1.925 29.2 2.55 2.75 0.000 2 -1.30 AFIL ag47c.dat CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 #----------------------------- SECTION -1.575 29.5 2.58 2.25 0.000 1 0 AFIL ag47c.dat CONTROL camber 1.0 0.70 0.0 1.0 0.11 1.0 CONTROL aileron -1.0 0.70 0.0 1.0 0.11 -1.0 # #============================================================== # SURFACE Stab 8 1.0 5 -1.5 ! Nchord Cspace # # reflect image wing about y=0 plane YDUPLICATE 0.00000 # # twist angle bias for whole surface ANGLE 0.00000 # # x,y,z bias for whole surface TRANSLATE 29.5000 0.00000 0.00000 SCALE 1.000 1.0 1.0 #-------------------------------------------------------------- # Xle Yle Zle chord angle Nspan Sspace SECTION -1.14 0.0 0.0 3.25 0.000 5 -1.50 AFIL ht22.dat CONTROL elevator 1.0 0.35 0.0 1.0 0.0 1.0 #----------------------------- SECTION -0.62 6.5 0.0 1.75 0.000 0 0 AFIL ht22.dat CONTROL elevator 1.0 0.35 0.0 1.0 0.0 1.0 # #============================================================== # SURFACE Rudder 8 1.0 14 0.75 ! Nchord Cspace # # x,y,z bias for whole surface TRANSLATE 33.3000 0.00000 0.00000 #-------------------------------------------------------------- # Xle Yle Zle chord angle Nspan Sspace SECTION -1.0 0.0 -3.25 2.50 0.000 4 1.50 CONTROL rudder 1.0 0.40 0.0 0.0 1.0 #----------------------------- SECTION -1.6 0.0 0.0 4.00 0.000 6 -1.50 CONTROL rudder 1.0 0.40 0.0 0.0 1.0 #----------------------------- SECTION -0.6 0.0 6.0 1.50 0.000 0 0 CONTROL rudder 1.0 0.40 0.0 0.0 1.0 #==============================================================