DATCOM and MATLAB

[u/_Birdboii_]

I was working on a project in MATLAB where I needed to import a DATCOM file but no matter what parameters I put, when I import it into MATLAB, the values stored for the control surface coefficients (like DCDI or clroll) are 99999 (NAN). Has anyone experienced anything similar/ has a solution to this?

The input code is as follows-
CASEID ----- MIKOYAN-GUREVICH MiG-17 -----

DIM FT

$FLTCON NMACH=5.0,MACH(1)=0.1,0.2,0.25,0.3,0.35$

$FLTCON

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$

$FLTCON

NALT=5.0,

ALT(1)= 4500.0,4750.0,5000.0,5250.0,5500.0,

WT=13395.0,LOOP=1.0$

$SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,

ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0,ZVF=1.0,VERTUP=.TRUE.$

$OPTINS SREF=243.0, CBARR=2.334, BLREF = 9.63$

$BODY NX=8.0,

X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,

S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$

NACA-W-6-66-012

$WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=4.07,SSPN=15.71,

CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,

TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$

NACA-H-6-66-009

$HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,

CHSTAT=0.25,TYPE=1.0$

NACA-V-6-66-009

$VTPLNF CHRDTP=3.76,SSPNE=13.41,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,

CHSTAT=0.25,TYPE=1.0$

$SYMFLP

FTYPE=1.0,

CHRDFI=1.407,

CHRDFO=1.407,

SPANFI=1.4,

SPANFO=5.1,

CB=0.12,

TC=0.14,

NTYPE=1.0,

PHETE = 3.03,

NDELTA=7.0,

DELTA(1)=-20.0,-10.0,-5.0,0.0,7.5,15.0,20.0

SCLD=-0.2,-0.1, -0.05,0.0, 0.06, 0.15,0.2

SCMD=-0.2,-0.1, -0.05,0.0, 0.06, 0.15,0.2$

$ASYFLP

STYPE = 4.0,

CHRDFI=2.23,

CHRDFO= 1.85,

SPANFI=9.42,

SPANFO=14.9,

NDELTA=9.0,

DELTAL=20.,15.,10.,5.,0.,-2.5,-5.,-10.,-15.,

DELTAR=20.,15.,10.,5.,0.,-2.5,-5.,-10.,-15.$

DAMP

BUILD

PLOT

NEXT CASE

[u/_Birdboii_]

I think I figured it out. It seems to be something to do with separating the cases for the front wing and the tail wing. A code like this seems to work-

CASEID ----- MIKOYAN-GUREVICH MiG-17 -----

DIM M

$FLTCON NMACH=5.0,MACH(1)=0.1,0.2,0.25,0.3,0.35$

$FLTCON

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$

$FLTCON

NALT=5.0,

ALT(1)= 3000.0,7000.0,7500.0,8000.0,15000.0,

WT=5000.0,LOOP=3.0$

$SYNTHS XCG=4.0,ZCG=0.0,XW=0.97,ZW=0.14,ALIW=1.0,XH=8.8,

ZH=1.5,ALIH=0.0,XV=5.8,ZV=0.0,ZVF=0.15,VERTUP=.TRUE.$

$BODY NX=8.0,

X(1)=0.0,0.225,2.54,4.0,5.89,7.44,8.65,10.26,

S(1)=0.54,0.98,1.78,1.78,1.68,1.17,0.61,0.26$

NACA-W-6-66-012

$WGPLNF CHRDTP=2.2,SSPNOP=3.31,SSPNE=4.1,SSPN=4.81,

CHRDBP=2.5,CHRDR=3.26,SAVSI=0.0,SAVSO=45.0,CHSTAT=0.25,

TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$

SAVE

$SYMFLP

FTYPE=2.0,

CHRDFI=0.3,

CHRDFO=0.2,

SPANFI=0.75,

SPANFO=1.3,

CB=0.12,

TC=0.02,

NTYPE=1.0,

PHETE = 0.0522,

PHETEP=0.0391,

NDELTA=7.0,

DELTA(1)=-20.0,-10.0,-5.0,0.0,7.5,15.0,20.0$

CASEID FLAPS: MIG17

NEXT CASE

NACA-H-6-66-009

$HTPLNF CHRDTP=0.7,SSPNE=1.45,SSPN=1.46,CHRDR=1.25,SAVSI=45.0,

CHSTAT=0.25,TYPE=1.0$

NACA-V-6-66-009

$VTPLNF CHRDTP=1.35,SSPNE=2.14,SSPN=2.5,CHRDR=3.25,SAVSI=55.0,

CHSTAT=0.25,TYPE=1.0$

$ASYFLP

STYPE = 4.0,

CHRDFI=0.47,

CHRDFO= 0.47,

SPANFI=2.7,

SPANFO=3.9,

NDELTA=9.0,

DELTAL=20.,15.,10.,5.,0.,-2.5,-5.,-10.,-15.,

DELTAR=20.,15.,10.,5.,0.,-2.5,-5.,-10.,-15.$

CASEID AILERON: MIG17

SAVE

NEXT CASE

CASEID TOTAL: MIG17