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Kjadam98

datcom not working? for AIR file coefficients?

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Hello, would someone mind helping me figure out why my ac3d model won't generate? This text works for the datcom outputs? I recently added flaps and ailerons...

Any help would be greatly appreciated! :D

$FLTCON NMACH = 1.0, MACH(1) = 0.13,
NALPHA=10.0, ALSCHD(1)=-4.0,-2.0,0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,
ALT=3000.0,
WT=583.0,LOOP=1.,$
$SYNTHS XCG=1.66872, ZCG=0.0,
XW=1.668, ZW=0.5222885, ALIW=8.5,
XH=5.137, ZH=0.0, ALIH=0.0,
XV=5.137, ZV=0.0,$
$BODY NX=8.0,
X(1)=0.0,0.298,1.396,3.084,3.681,4.128,4.725,5.372,
S(1)=0.0001,0.0486,0.856,0.856,0.497,0.278,0.095,0.031,$
NACA-W-4-2412
NACA-H-6-66-009
NACA-V-6-66-009
$WGPLNF CHRDTP=1.31,
SSPNE=4.5, SSPN=4.725,
CHRDR=1.435,
SAVSO=0.0,
CHSTAT=0.25,
TWISTA=0.0,
DHDADI=1.0,
TYPE=1.0,$
$SYMFLP FTYPE=1.0, NTYPE=1.0,
NDELTA=9.0, DELTA(1)=-20.0,-15.0,-10.0,-5.0,0.0,5.0,10.0,13.0,16.0,
CHRDFI=0.298, CHRDFO=0.249, SPANFI=0.298, SPANFO=2.09,$
$ASYFLP STYPE=4.0,NDELTA=9.0,
DELTAL(1)=-32.0,-20.0,-10.0,-5.0,0.0, 5.0, 10.0, 20.0, 32.0,

DELTAR(1)= 32.0, 20.0, 10.0, 5.0,0.0,-5.0,-10.0,-20.0,-32.0,

SPANFI=2.08895, SPANFO=4.72501, CHRDFI=0.2487, CHRDFO=0.1492,$
$HTPLNF CHRDTP=0.72,
SSPNE=1.17, SSPN=1.27,
CHRDR=0.65,
SAVSI=0.06,
CHSTAT=0.25,
TYPE=1.0,$
$SYMFLP FTYPE=1.0, NTYPE=1.0,
NDELTA=9.0, DELTA(1)=-20.0,-15.0,-10.0,-5.0,0.0,5.0,10.0,13.0,16.0,
CHRDFI=0.4476, CHRDFO=0.2489, SPANFI=0.09947, SPANFO=1.2434,$
$VTPLNF CHRDTP=0.62,
SSPNE=1.08, SSPN=1.08,
CHRDR=0.982,
SAVSI=25.0,
CHSTAT=0.25,
TYPE=1.0,$
DIM M
BUILD
PLOT
CASEID IKARUS C42
SAVE
NEXT CASE

Also, how can I get all the coefficients needed for the AIR file?

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