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aircraft.avl
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aircraft.avl
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AIRCRAFT
#======================================================
#------------------- Geometry File --------------------
#======================================================
# AVL Conventions
# SI Used: m, kg, etc
#Mach
0.1
#IYsym IZsym Zsym
0 0 0
#Sref Cref b_wing
1.13047707106 0.361159860776 5.99996825959
#Xref Yref Zref
0.0837252385711 0.0 0.0
# CDp
0.011600
#======================================================
#--------------------- Main Wing ----------------------
#======================================================
SURFACE
Wing
#Nchordwise Cspace [Nspan Sspace]
7 1.0 20 -2.0
YDUPLICATE
0.0
SCALE
1.0 1.0 1.0
TRANSLATE
0.0 0.0 0.0
ANGLE
0.0
#------------------------------------------------------
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
0.0 0.0 0 0.334900954284 0.0 5 3
AFILE
airfoils/A_1.dat
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
0.0 0.749996032448 0 0.210092616592 0.0 5 3
AFILE
airfoils/A_2.dat
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
0.0 1.4999920649 0 0.136024742198 0.0 5 3
AFILE
airfoils/A_3.dat
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
0.0 2.24998809734 0 0.112697331104 0.0 5 3
AFILE
airfoils/A_4.dat
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
0.0 2.99998412979 0 0.140110383308 0.0 5 3
AFILE
airfoils/A_5.dat
#======================================================
#------------------- Horizontal Tail ------------------
#======================================================
SURFACE
HorizontalTail
#Nchordwise Cspace Nspan Sspace
10 1.0 20 2
YDUPLICATE
0.0
SCALE
1.0 1.0 1.0
TRANSLATE
0.0 0.0 0.0
ANGLE
0
#------------------TAIL ROOT/ELEVATOR------------------
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
1.60247523857 0.0 0 0.325 0.0
NACA
0012
CLAF
1.1078
CONTROL
#surface gain xhinge hvec SgnDup
Elevator -1.00 0.0 0 1 0 1.00
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
1.60247523857 0.52 0 0.325 0.0
NACA
0012
CLAF
1.1078
CONTROL
#surface gain xhinge hvec SgnDup
Elevator -1.00 0.0 0 1 0 1.00
#======================================================
#------------------- Vertical Tail --------------------
#======================================================
SURFACE
VerticalTail
# Nchordwise Cspace Nspanwise Sspace
10 1.00 10 -2.0
# YDUPLICATE
# 0.0
#Xscale Yscale Zscale
SCALE
1.0 1.0 1.0
ANGLE
0.0
TRANSLATE
0.0 0.0 0.0
INDEX
2
#----------------------ROOT/RUDDER---------------------
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
1.60247523857 0 0.0 0.325 0.0
NACA
0012
CLAF
1.1078
CONTROL
#surface gain xhinge hvec SgnDup
Rudder 1.00 0.5 0 0 1 -1.00
SECTION
#Xle Yle Zle | Chord Ainc Nspan Sspace
1.60247523857 0 0.296 0.325 0.0
NACA
0012
CLAF
1.1078
CONTROL
#surface gain xhinge hvec SgnDup
Rudder 1.00 0.5 0 0 1 -1.00
# -- END OF FILE --