Bring DATCOM file into MATLAB environment
aero = datcomimport(file)
aero = datcomimport(file, usenan)
aero = datcomimport(file, usenan, verbose)
aero = datcomimport(file, usenan, verbose, filetype)
aero = datcomimport(file)
takes a file name,
file
, as a character vector or string (or a cell array of file names as
character vectors or strings), and imports aerodynamic data from file
into a
cell array of structures, aero
. Before reading the DATCOM file, the function
initializes values to 99999 to show when there is not a full set of data for the DATCOM case.
aero = datcomimport(file, usenan)
is
an alternate method allowing the replacement of data points with NaN
or zero where no DATCOM methods exist or where the method is not applicable.
The default value for usenan
is true
.
aero = datcomimport(file, usenan, verbose)
is
an alternate method to display the status of the DATCOM file being
read. The default value for verbose
is 2
,
which displays a wait bar. Other options are 0
,
which displays no information, and 1
, which displays
text to the MATLAB^{®} Command Window.
aero = datcomimport(file, usenan, verbose, filetype)
is
an alternate method that allows you to specify which type of DATCOM
file to read. The possible values are listed in this table:
filetype Value  Output File from DATCOM 

6  (Default) 
21 

42 

When filetype
is 6
, the
function reads the for006.dat
file output by DATCOM.
If filetype
is 21
, the
function collates the breakpoints and data from all the cases and
appends them as the last entry of aero
.
When filetype
is 21
, the
function reads the for021.dat
file output by DATCOM
2007.
When file type is 42
, the function reads
the for042.csv
file output by DATCOM 2008, DATCOM
2011, and DATCOM 2014.
Fields for the 1976, 1999, 2007, 2008, 2011, and 2014 versions
of the type 6
output files:
Fields for 2007, 2008, 2011, and 2014 versions of the type 21 output file:
Fields for 2008, 2011, and 2014 versions of the type 42 output file are described in:
The fields of aero
depend
on the data within the DATCOM file.
Common Fields for the 1976 Version (File Type 6)
Field  Description  Default 

case  Character vector containing the case ID.  [] 
mach  Array of Mach numbers.  [] 
alt  Array of altitudes.  [] 
alpha  Array of angles of attack.  [] 
nmach  Number of Mach numbers.  0 
nalt  Number of altitudes.  0 
nalpha  Number of angles of attack.  0 
rnnub  Array of Reynolds numbers.  [] 
hypers  Logical denoting, when true , that mach numbers
above tsmach are hypersonic. Default values are
supersonic.  false 
loop  Scalar denoting the type of looping done to generate the DATCOM
file. When loop is 1 , mach and alt are
varied together. When loop is 2 , mach varies
while alt is fixed. Altitude is then updated and
Mach numbers are cycled through again. When loop is 3 , mach is
fixed while alt varies. mach is
then updated and altitudes are cycled through again.  1 
sref  Scalar denoting the reference area for the case.  [] 
cbar  Scalar denoting the longitudinal reference length.  [] 
blref  Scalar denoting the lateral reference length.  [] 
dim  Character vector denoting the specified system of units for the case.  'ft' 
deriv  Character vector denoting the specified angle units for the case.  'deg' 
stmach  Scalar value setting the upper limit of subsonic Mach numbers.  0.6 
tsmach  Scalar value setting the lower limit of supersonic Mach numbers.  1.4 
save  Logical denoting whether the input values for this case are used in the next case.  false 
stype  Scalar denoting the type of asymmetric flap for the case.  [] 
trim  Logical denoting the reading of trim data for the case. When
trim runs are read, this value is set to true .  false 
damp  Logical denoting the reading of dynamic derivative data for
the case. When dynamic derivative runs are read, this value is set
to true .  false 
build  Scalar denoting the reading of build data for the case. When build runs are read, this value is set to 10.  1 
part  Logical denoting the reading of partial data for the case.
When partial runs are written for each Mach number, this value is
set to true .  false 
highsym  Logical denoting the reading of symmetric flap highlift data
for the case. When symmetric flap runs are read, this value is set
to true .  false 
highasy  Logical denoting the reading of asymmetric flap highlift data
for the case. When asymmetric flap runs are read, this value is set
to true .  false 
highcon  Logical denoting the reading of control/trim tab highlift
data for the case. When control/trim tab runs are read, this value
is set to true .  false 
tjet  Logical denoting the reading of transversejet control data
for the case. When transversejet control runs are read, this value
is set to true .  false 
hypeff  Logical denoting the reading of hypersonic flap effectiveness
data for the case. When hypersonic flap effectiveness runs are read,
this value is set to true .  false 
lb  Logical denoting the reading of low aspect ratio wing or lifting
body data for the case. When low aspect ratio wing or lifting body
runs are read, this value is set to true .  false 
pwr  Logical denoting the reading of power effects data for the
case. When power effects runs are read, this value is set to true .  false 
grnd  Logical denoting the reading of ground effects data for the
case. When ground effects runs are read, this value is set to true .  false 
wsspn  Scalar denoting the semispan theoretical panel for wing. This value is used to determine if the configuration contains a canard.  1 
hsspn  Scalar denoting the semispan theoretical panel for horizontal tail. This value is used to determine if the configuration contains a canard.  1 
ndelta  Number of control surface deflections: delta , deltal ,
or deltar .  0 
delta  Array of controlsurface streamwise deflection angles.  [] 
deltal  Array of left lifting surface streamwise control deflection angles, which are defined positive for trailingedge down.  [] 
deltar  Array of right lifting surface streamwise control deflection angles, which are defined positive for trailingedge down.  [] 
ngh  Scalar denoting the number of ground altitudes.  0 
grndht  Array of ground heights.  [] 
config  Structure of logicals denoting whether the case contains horizontal tails.  false , as follows.config.downwash = false; config.body = false; config.wing = false; config.htail = false; config.vtail = false; config.vfin = false; 
version  Version of DATCOM file.  1976 
Static Longitude and Lateral Stability Fields Available for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

cd  Drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt , build , grndht , delta 
cl  Lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt , build , grndht , delta 
cm  Pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , alt , build , grndht , delta 
cn  Normalforce coefficients, which are defined positive for a normal force in the +Z direction.  alpha , mach , alt , build , grndht , delta 
ca  Axialforce coefficients, which are defined positive for a normal force in the +X direction.  alpha , mach , alt , build , grndht , delta 
xcp  Distances between moment reference center and the center of pressure divided by the longitudinal reference length. Distances are defined positive for a location forward of the center of gravity.  alpha , mach , alt , build , grndht , delta 
cla  Derivatives of lift coefficients relative to alpha .
 alpha , mach , alt , build , grndht , delta 
cma  Derivatives of pitchingmoment coefficients relative to alpha .
 alpha , mach , alt , build , grndht , delta 
cyb  Derivatives of sideforce coefficients relative to sideslip angle.  alpha , mach , alt , build , grndht , delta 
cnb  Derivatives of yawingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build , grndht , delta 
clb  Derivatives of rollingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build , grndht , delta 
qqinf  Ratios of dynamic pressure at the horizontal tail to the freestream value.  alpha , mach , alt , build , grndht , delta 
eps  Downwash angle at horizontal tail in degrees.  alpha , mach , alt , build , grndht , delta 
depsdalp  Downwash angle relative to angle of attack.  alpha , mach , alt , build , grndht , delta 
Dynamic Derivative Fields for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

clq  Lift force derivatives due to pitch rate.  alpha , mach , alt , build 
cmq  Pitchingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
clad  Liftforce derivatives due to rate of angle of attack.  alpha , mach , alt , build 
cmad  Pitchingmoment derivatives due to rate of angle of attack.  alpha , mach , alt , build 
clp  Rollingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cyp  Lateralforce derivatives due to roll rate.  alpha , mach , alt , build 
cnp  Yawingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cnr  Yawingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
clr  Rollingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
HighLift and Control Fields for Symmetric Flaps for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

dcl_sym  Incremental lift coefficients due to deflection of control surface, valid in the linearlift angle of attack range.  delta , mach , alt 
dcm_sym  Incremental pitchingmoment coefficients due to deflection of control surface, valid in the linearlift angle of attack range.  delta , mach , alt 
dclmax_sym  Incremental maximum lift coefficients.  delta , mach , alt 
dcdmin_sym  Incremental minimum drag coefficients due to control or flap deflection.  delta , mach , alt 
clad_sym  Liftcurve slope of the deflected, translated surface.  delta , mach , alt 
cha_sym  Controlsurface hingemoment derivatives due to angle of attack. These derivatives, when defined positive, tend to rotate the flap trailing edge down.  delta , mach , alt 
chd_sym  Controlsurface hingemoment derivatives due to control deflection. When defined positive, these derivatives tend to rotate the flap trailing edge down.  delta , mach , alt 
dcdi_sym  Incremental induced drag coefficients due to flap detection.  alpha , delta , mach , alt 
HighLift and Control Fields Available for Asymmetric Flaps for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

xsc  Streamwise distances from wing leading edge to spoiler tip.  delta , mach , alt 
hsc  Projected height of spoiler measured from normal to airfoil meanline.  delta , mach , alt 
ddc  Projected height of deflector for spoilerslotdeflector control.  delta , mach , alt 
dsc  Projected height of spoiler control.  delta , mach , alt 
clroll  Incremental rollingmoment coefficients due to asymmetrical deflection of control surface. The coefficients are defined positive when right wing is down.  delta , mach , and alt ,
or alpha , delta , mach ,
and alt for differential horizontal stabilizer 
cn_asy  Incremental yawingmoment coefficients due to asymmetrical deflection of control surface. The coefficients are defined positive when nose is right.  delta , mach , and alt ,
or alpha , delta , mach ,
and alt for plain flaps 
HighLift and Control Fields Available for Control/Trim Tabs for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

fc_con  Stick forces or stick force coefficients.  alpha , delta , mach , alt 
fhmcoeff_free  Flaphinge moment coefficients tab free.  alpha , delta , mach , alt 
fhmcoeff_lock  Flaphinge moment coefficients tab locked.  alpha , delta , mach , alt 
fhmcoeff_gear  Flaphinge moment coefficients due to gearing.  alpha , delta , mach , alt 
ttab_def  Trimtab deflections for zero stick force.  alpha , delta , mach , alt 
HighLift and Control Fields Available for Trim for the 1976 Version (File Type 6)
Field  Matrix of...  Function of... 

cl_utrim  Untrimmed lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt 
cd_utrim  Untrimmed drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt 
cm_utrim  Untrimmed pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , alt 
delt_trim  Trimmed controlsurface streamwise deflection angles.  alpha , mach , alt 
dcl_trim  Trimmed incremental lift coefficients in the linearlift angle of attack range due to deflection of control surface.  alpha , mach , alt 
dclmax_trim  Trimmed incremental maximum lift coefficients.  alpha , mach , alt 
dcdi_trim  Trimmed incremental induced drag coefficients due to flap deflection.  alpha , mach , alt 
dcdmin_trim  Trimmed incremental minimum drag coefficients due to control or flap deflection.  alpha , mach , alt 
cha_trim  Trimmed controlsurface hingemoment derivatives due to angle of attack.  alpha , mach , alt 
chd_trim  Trimmed controlsurface hingemoment derivatives due to control deflection.  alpha , mach , alt 
cl_tailutrim  Untrimmed stabilizer lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt 
cd_tailutrim  Untrimmed stabilizer drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt 
cm_tailutrim  Untrimmed stabilizer pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , alt 
hm_tailutrim  Untrimmed stabilizer hingemoment coefficients, which are defined positive for a stabilizer rotation with leading edge up and trailing edge down.  alpha , mach , alt 
aliht_tailtrim  Stabilizer incidence required to trim.  alpha , mach , alt 
cl_tailtrim  Trimmed stabilizer lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt 
cd_tailtrim  Trimmed stabilizer drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt 
cm_tailtrim  Trimmed stabilizer pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , alt 
hm_tailtrim  Trimmed stabilizer hingemoment coefficients, which are defined positive for a stabilizer rotation with leading edge up and trailing edge down.  alpha , mach , alt 
cl_trimi  Lift coefficients at trim incidence. These coefficients are defined positive for an upacting load.  alpha , mach , alt 
cd_trimi  Drag coefficients at trim incidence. These coefficients are defined positive for an aftacting load.  alpha , mach , alt 
Transverse Jet Control Fields for the 1976 Version (File Type 6)
Field  Description  Stored with Indices of... 

time  Matrix of times.  mach , alt , alpha 
ctrlfrc  Matrix of control forces.  mach , alt , alpha 
locmach  Matrix of local Mach numbers.  mach , alt , alpha 
reynum  Matrix of Reynolds numbers.  mach , alt , alpha 
locpres  Matrix of local pressures.  mach , alt , alpha 
dynpres  Matrix of dynamic pressures.  mach , alt , alpha 
blayer  Cell array of character vectors containing the state of the boundary layer.  mach , alt , alpha 
ctrlcoeff  Matrix of control force coefficients.  mach , alt , alpha 
corrcoeff  Matrix of corrected force coefficients.  mach , alt , alpha 
sonicamp  Matrix of sonic amplification factors.  mach , alt , alpha 
ampfact  Matrix of amplification factors.  mach , alt , alpha 
vacthr  Matrix of vacuum thrusts.  mach , alt , alpha 
minpres  Matrix of minimum pressure ratios.  mach , alt , alpha 
minjet  Matrix of minimum jet pressures.  mach , alt , alpha 
jetpres  Matrix of jet pressures.  mach , alt , alpha 
massflow  Matrix of mass flow rates.  mach , alt , alpha 
propelwt  Matrix of propellant weights.  mach , alt , alpha 
Hypersonic Fields for the 1976 Version (File Type 6)
Field  Matrix of...  Stored with Indices of... 

df_normal  Increments in normal force per spanwise foot of control.  alpha , delta , mach 
df_axial  Increments in axial force per spanwise foot of control.  alpha , delta , mach 
cm_normal  Increments in pitching moment due to normal force per spanwise foot of control.  alpha , delta , mach 
cm_axial  Increments in pitching moment due to axial force per spanwise foot of control.  alpha , delta , mach 
cp_normal  Center of pressure locations of normal force.  alpha , delta , mach 
cp_axial  Center of pressure locations of axial force.  alpha , delta , mach 
Auxiliary and Partial Fields Available for the 1976 Version (File Type 6)
Field  Matrix of...  Stored with Indices of... 

wetarea_b  Body wetted area.  mach , alt , number of
runs 
xcg_b  Longitudinal locations of the center of gravity.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
zcg_b  Vertical locations of the center of gravity.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
basearea_b  Body base area.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
cd0_b  Body zero lift drags.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
basedrag_b  Body base drags.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
fricdrag_b  Body friction drags.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
presdrag_b  Body pressure drags.  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
lemac  Leading edge mean aerodynamic chords.  mach , alt 
sidewash  sidewash  mach , alt 
hiv_b_w  ivb(w)  alpha , mach , alt 
hiv_w_h  ivw(h)  alpha , mach , alt 
hiv_b_h  ivb(h)  alpha , mach , alt 
gamma  gamma*2*pi*alpha*v*r  alpha , mach , alt 
gamma2pialpvr  gamma*(2*pi*alpha*v*r)t  alpha , mach , alt 
clpgammacl0  clp(gamma=cl=0)  mach , alt 
clpgammaclp  clp(gamma)/cl (gamma=0)  mach , alt 
cnptheta  cnp/theta  mach , alt 
cypgamma  cyp/gamma  mach , alt 
cypcl  cyp/cl (cl=0)  mach , alt 
clbgamma  clb/gamma  mach , alt 
cmothetaw  (cmo/theta)w  mach , alt 
cmothetah  (cmo/theta)h  mach , alt 
espeff  (epsoln)eff  alpha , mach , and alt 
despdalpeff  d(epsoln)/d(alpha) eff  alpha , mach , alt 
dragdiv  drag divergence mach number  mach , alt 
cd0mach  Four Mach numbers for the zero lift drag.  index , mach , alt 
cd0  Four zero lift drags.  index , mach , alt 
clbclmfb_****  (clb/cl)mfb , where **** is
either wb (wingbody) or bht (bodyhorizontal
tail).  mach , alt . 
cnam14_****  (cna)m=1.4 , where **** is
either wb (wingbody) or bht (bodyhorizontal
tail).  mach ,alt 
area_*_**  Areas, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
taperratio_*_**  Taper ratios, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
aspectratio_*_**  Aspect ratios, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
qcsweep_*_**  Quarter chord sweeps, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
mac_*_**  Mean aerodynamic chords, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
qcmac_*_**  Quarter chord x(mac) , where * is
either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
ymac_*_**  y(mac) , where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
cd0_*_**  Zero lift drags, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
friccoeff_*_**  Friction coefficients, where * is either w (wing), ht (horizontal
tail), vt (vertical tail), or vf (ventral
fin) and ** is either tt (total
theoretical), ti (theoretical inboard), te (total
exposed), ei (exposed inboard), or o (outboard).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
cla_b_***  clab(***) , where *** is
either w (wing) or ht (stabilizer).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
cla_***_b  cla***(b) , where *** is
either w (wing) or ht (stabilizer).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
k_b_***  kb(***) , where *** is
either w (wing) or ht (stabilizer).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
k_***_b  k***(b) , where *** is
either w (wing) or ht (stabilizer).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
xacc_b_***  xac/cb(***) , where *** is
either w (wing) or ht (stabilizer).  mach , alt , number of
runs (normally 1, 2 for hypers = true ) 
cdlcl2_***  cdl/cl^2 , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
clbcl_***  clb/cl , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
fmach0_***  Force break Mach numbers with zero sweep, where *** is
either w (wing) or ht (stabilizer).  mach , alt 
fmach_***  Force break Mach numbers with sweep, where *** is
either w (wing) or ht (stabilizer).  mach , alt 
macha_***  mach(a) , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
machb_***  mach(b) , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
claa_***  cla(a) , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
clab_***  cla(b) , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
clbm06_***  (clb/cl)m=0.6 , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
clbm14_***  (clb/cl)m=1.4 , where *** is
either w (wing) or ht (stabilizer).  mach , alt 
clalpmach_***  Five Mach numbers for the lift curve slope, where *** is
either w (wing) or ht (stabilizer).  index , mach , alt 
clalp_***  Five liftcurve slope values, where *** is
either w (wing) or ht (stabilizer).  index , mach , alt 
Common Fields for the 1999 Version (File Type 6)
Field  Description  Default 

case  Character vector containing the case ID.  [] 
mach  Array of Mach numbers.  [] 
alt  Array of altitudes.  [] 
alpha  Array of angles of attack.  [] 
nmach  Number of Mach numbers.  0 
nalt  Number of altitudes.  1 
nalpha  Number of angles of attack.  0 
rnnub  Array of Reynolds numbers.  [] 
beta  Scalar containing sideslip angle.  0 
phi  Scalar containing aerodynamic roll angle.  0 
loop  Scalar denoting the type of looping performed to generate the
DATCOM file. When loop is 1 , mach and alt are
varied together. The only loop option for the 1999 version of DATCOM
is loop is equal to 1 .  1 
sref  Scalar denoting the reference area for the case.  [] 
cbar  Scalar denoting the longitudinal reference length.  [] 
blref  Scalar denoting the lateral reference length.  [] 
dim  Character vector denoting the specified system of units for the case.  'ft' 
deriv  Character vector denoting the specified angle units for the case.  'deg' 
save  Logical denoting whether the input values for this case are used in the next case.  false 
stype  Scalar denoting the type of asymmetric flap for the case.  [] 
trim  Logical denoting the reading of trim data for the case. When
trim runs are read, this value is set to true .  false 
damp  Logical denoting the reading of dynamic derivative data for
the case. When dynamic derivative runs are read, this value is set
to true .  false 
build  Scalar denoting the reading of build data for the case. When build runs are read, this value is set to the number of build runs depending on the vehicle configuration.  1 
part  Logical denoting the reading of partial data for the case.
When partial runs are written for each Mach number, this value is
set to true .  false 
hypeff  Logical denoting the reading of hypersonic data for the case.
When hypersonic data is read, this value is set to true .  false 
ngh  Scalar denoting the number of ground altitudes.  0 
nolat  Logical denoting the calculation of the lateraldirection derivatives is inhibited.  false 
config  Structure of logicals and structures detailing the case configuration and fin deflections.  config.body = false config.fin1.avail = false; config.fin1.npanel = []; config.fin1.delta = []; config.fin2.avail = false; config.fin2.npanel = []; config.fin2.delta = []; config.fin3.avail = false; config.fin3.npanel = []; config.fin3.delta = []; config.fin4.avail = false; config.fin4.npanel = []; config.fin4.delta = []; 
version  Version of DATCOM file.  1999 
Static Longitude and Lateral Stability Fields Available for the 1999 Version (File Type 6)
Field  Matrix of...  Function of... 

cd  Drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt , build 
cl  Lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt , build 
cm  Pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach alt , build 
cn  Normalforce coefficients, which are defined positive for a normal force in the +Z direction.  alpha , mach , alt , build 
ca  Axialforce coefficients, which are defined positive for a normal force in the +X direction.  alpha , mach , alt , build 
xcp  Distances between moment reference center and the center of pressure divided by the longitudinal reference length. These distances are defined positive for a location forward of the center of gravity.  alpha , mach , alt , build 
cna  Derivatives of normalforce coefficients relative to alpha .
 alpha , mach , alt , build 
cma  Derivatives of pitchingmoment coefficients relative to alpha .
 alpha , mach , alt , build 
cyb  Derivatives of sideforce coefficients relative to sideslip angle.  alpha , mach , alt , build 
cnb  Derivatives of yawingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build 
clb  Derivatives of rollingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build 
clod  Ratios of lift coefficient to drag coefficient.  alpha , mach , alt , build 
cy  Sideforce coefficients.  alpha , mach , alt , build 
cln  Yawingmoment coefficient in bodyaxis.  alpha , mach , alt , build 
cll  Rollingmoment coefficient in bodyaxis.  alpha , mach , alt , build 
Dynamic Derivative Fields for the 1999 Version (File Type 6)
Field  Matrix of...  Function of... 

cnq  Normalforce derivatives due to pitch rate.  alpha , mach , alt , build 
cmq  Pitchingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
caq  Axialforce derivatives due to pitch rate.  alpha , mach , alt , build 
cnad  Normalforce derivatives due to rate of angle of attack.  alpha , mach , alt , build 
cmad  Pitchingmoment derivatives due to rate of angle of attack.  alpha , mach , alt , build 
clp  Rollingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cyp  Lateral force derivatives due to roll rate.  alpha , mach , alt , build 
cnp  Yawingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cnr  Yawingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
clr  Rollingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
cyr  Side force derivatives due to yaw rate.  alpha , mach , alt , build 
Common Fields for the 2007, 2008, 2011, and 2014 Versions (File Type 6)
Field  Description  Default 

case  Character vector containing the case ID.  [] 
mach  Array of Mach numbers.  [] 
alt  Array of altitudes.  [] 
alpha  Array of angles of attack.  [] 
nmach  Number of Mach numbers.  0 
nalt  Number of altitudes.  1 
nalpha  Number of angles of attack.  0 
rnnub  Array of Reynolds numbers.  [] 
beta  Scalar containing sideslip angle. NoteThis value does not appear correctly for the 2014 version. It always displays 0.  0 
phi  Scalar containing aerodynamic roll angle.  0 
loop  Scalar denoting the type of looping performed to generate the
DATCOM file. When loop is 1 , mach and alt are
varied together. The only loop option for the 2007 version of DATCOM
is loop , equal to 1 .  1 
sref  Scalar denoting the reference area for the case.  [] 
cbar  Scalar denoting the longitudinal reference length.  [] 
blref  Scalar denoting the lateral reference length.  [] 
dim  Character vector denoting the specified system of units for the case.  'ft' 
deriv  Character vector denoting the specified angle units for the case.  'deg' 
save  Logical denoting whether the input values for this case are used in the next case.  false 
stype  Scalar denoting the type of asymmetric flap for the case.  [] 
trim  Logical denoting the reading of trim data for the case. When
trim runs are read, this value is set to true .  false 
damp  Logical denoting the reading of dynamic derivative data for
the case. When dynamic derivative runs are read, this value is set
to true .  false 
build  Scalar denoting the reading of build data for the case. When build runs are read, this value is set to the number of build runs depending on the vehicle configuration.  1 
part  Logical denoting the reading of partial data for the case.
When partial runs are written for each Mach number, this value is
set to true .  false 
hypeff  Logical denoting the reading of hypersonic data for the case.
When hypersonic data is read, this value is set to true .  false 
ngh  Scalar denoting the number of ground altitudes.  0 
nolat  Logical denoting the calculation of the lateraldirection derivatives is inhibited.  false 
config  Structure of logicals and structures detailing the case configuration and fin deflections.  config.body = false; config.fin1.avail = false; config.fin1.npanel = []; config.fin1.delta = []; config.fin2.avail = false; config.fin2.npanel = []; config.fin2.delta = []; config.fin3.avail = false; config.fin3.npanel = []; config.fin3.delta = []; config.fin4.avail = false; config.fin4.npanel = []; config.fin4.delta = []; 
nolat_namelist  Logical denoting the calculation of the lateraldirection derivatives is inhibited in the DATCOM input case.  false 
version  Version of DATCOM file.  2007 
Static Longitude and Lateral Stability Fields Available for the 2007, 2008, 2011, and 2014 Versions (File Type 6)
Field  Matrix of...  Function of... 

cd  Drag coefficients, which are defined positive for an aftacting load.  alpha , mach , alt , build 
cl  Lift coefficients, which are defined positive for an upacting load.  alpha , mach , alt , build 
cm  Pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach alt , build 
cn  Normalforce coefficients, which are defined positive for a normal force in the +Z direction.  alpha , mach , alt , build 
ca  Axialforce coefficients, which are defined positive for a normal force in the +X direction.  alpha , mach , alt , build 
xcp  Distances between moment reference center and the center of pressure divided by the longitudinal reference length. These distances are defined positive for a location forward of the center of gravity.  alpha , mach , alt , build 
cna  Derivatives of normalforce coefficients relative to alpha .
 alpha , mach , alt , build 
cma  Derivatives of pitchingmoment coefficients relative to alpha .
 alpha , mach , alt , build 
cyb  Derivatives of sideforce coefficients relative to sideslip angle.  alpha , mach , alt , build 
cnb  Derivatives of yawingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build 
clb  Derivatives of rollingmoment coefficients relative to sideslip angle.  alpha , mach , alt , build 
clod  Ratios of lift coefficient to drag coefficient.  alpha , mach , alt , build 
cy  Sideforce coefficients.  alpha , mach , alt , build 
cln  Yawingmoment coefficient in bodyaxis.  alpha , mach , alt , build 
cll  Rollingmoment coefficient in bodyaxis.  alpha , mach , alt , build 
Dynamic Derivative Fields for the 2007, 2008, 2011, and 2014 Versions (File Type 6)
Field  Matrix of...  Function of... 

cnq  Normalforce derivatives due to pitch rate.  alpha , mach , alt , build 
cmq  Pitchingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
caq  Axialforce derivatives due to pitch rate.  alpha , mach , alt , build 
cnad  Normalforce derivatives due to rate of angle of attack.  alpha , mach , alt , build 
cmad  Pitchingmoment derivatives due to rate of angle of attack.  alpha , mach , alt , build 
clp  Rollingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cyp  Lateralforce derivatives due to roll rate.  alpha , mach , alt , build 
cnp  Yawingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cnr  Yawingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
clr  Rollingmoment derivatives due to yaw rate  alpha , mach , alt , build 
cyr  Sideforce derivatives due to yaw rate.  alpha , mach , alt , build 
For 2008, 2011, and 2014, the version is 2008. There are no discernible differences in the outputs of these versions.
Common Fields for the 2007, 2008, 2011, and 2014 Versions (File Type 21)
Field  Description  Default 

mach  Array of Mach numbers.  [] 
alt  Array of altitudes.  [] 
alpha  Array of angles of attack.  [] 
nalpha  Number of angles of attack.  0 
beta  Scalar containing sideslip angle. NoteThis value does not appear correctly for the 2014 version. It always displays 0.  0 
total_col  Scalar denoting the type of looping performed to generate the
DATCOM file. When loop is 1, mach and alt are
varied together. The only loop option for the 2007, 2008, 2011, and
2014 versions of DATCOM is loop equal to 1 .  [] 
deriv_col  Logical denoting the calculation of the lateraldirection derivatives is inhibited.  0 
config  Structure of logicals and structures detailing the case configuration and fin deflections.  config.fin1.delta = zeros(1,8); config.fin2.delta = zeros(1,8); config.fin3.delta = zeros(1,8); config.fin4.delta = zeros(1,8); 
version  Version of DATCOM file.  2007 
Static Longitude and Lateral Stability Fields Available for the 2007, 2008, 2011, and 2014 Versions (File Type 21)
Field  Matrix of...  Function of... 

cn  Normalforce coefficients, which are defined positive for a normal force in the +Z direction.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cm  Pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
ca  Axialforce coefficients, which are defined positive for a normal force in the +X direction.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cy  Sideforce coefficients.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cln  Yawingmoment coefficient in bodyaxis.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cll  Rollingmoment coefficient in bodyaxis.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
Dynamic Derivative Fields for the 2007, 2008, 2011, and 2014 Versions (File Type 21)
Field  Matrix of...  Function of... 

cnad  Normalforce derivatives due to rate of angle of attack.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cmad  Pitchingmoment derivatives due to rate of angle of attack.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cnq  Normalforce derivatives due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cmq  Pitchingmoment derivatives due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
caq  Axialforce derivatives due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cyq  Sideforce due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
clnq  Yawingmoment due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cllq  Rollingmoment due to pitch rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cnp  Yawingmoment derivatives due to roll rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cap  Axialforce due to roll rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cyp  Lateralforce derivatives due to roll rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
clnp  Yawingmoment due to roll rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cllp  Rollingmoment due to roll rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cnr  Yawingmoment derivatives due to yaw rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
car  Axialforce due to yaw rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cyr  Sideforce derivatives due to yaw rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
clnr  Yawingmoment due to yaw rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
cllr  Rollingmoment due to yaw rate.  alpha , mach , alt , beta , config.fin1.delta , config.fin2.delta , config.fin3.delta , config.fin4.delta 
Fields for the 2008, 2011, and 2014 Version (File Type 42)
Field  Description  Default 

case  Character vector containing the case ID.  [] 
totalCol  Scalar containing number of columns of data in file.  [] 
mach  Array of Mach numbers.  [] 
alt  Array of altitudes.  [] 
alpha  Array of angles of attack.  [] 
nmach  Number of Mach numbers.  0 
nalpha  Number of angles of attack.  0 
rnnub  Array of Reynolds numbers.  [] 
q  Dynamic pressure.  [] 
beta  Scalar containing sideslip angle. NoteThis value does not appear correctly for the 2014 version. It always displays 0.  0 
phi  Scalar containing aerodynamic roll angle.  0 
sref  Scalar denoting the reference area for the case.  [] 
cbar  Scalar denoting the longitudinal reference length.  [] 
blref  Scalar denoting the lateral reference length.  [] 
xcg  Distance from nose to center of gravity.  [] 
xmrp  Distance from nose to center of gravity, measured in calibers.  [] 
deriv  Character vector denoting the specified angle units for the case.  'deg' 
trim  Logical denoting the reading of trim data for the case. When
trim runs are read, this value is set to true .
 false 
damp  Logical denoting the reading of dynamic derivative data for
the case. When dynamic derivative runs are read, this value is set
to true .  false 
build  Scalar denoting the reading of partial data for the case. This value is set to the number of partial runs depending on the vehicle configuration.  1 
part  Logical denoting the reading of partial data for the case.
When partial runs are written for each Mach number, this value is
set to true .  false 
nolat  Logical denoting the calculation of the lateraldirection derivatives is inhibited.  true 
config  Structure of logicals and structures detailing the case configuration and fin deflections.  config.body = false; config.fin1.avail = false; config.fin1.npanel = []; config.fin1.delta = []; config.fin2.avail = false; config.fin2.npanel = []; config.fin2.delta = []; config.fin3.avail = false; config.fin3.npanel = []; config.fin3.delta = []; config.fin4.avail = false; config.fin4.npanel = []; 
version  Version of DATCOM file.  2008 
Static Longitude and Lateral Stability Fields Available for the 2008, 2011, and 2014 Versions (File Type 42)
Field  Matrix of...  Function of... 

delta  Trim deflection angles.  alpha , mach 
cd  Drag coefficients, which are defined positive for an aftacting load.  alpha , mach , build 
cl  Lift coefficients, which are defined positive for an upacting load.  alpha , mach , build 
cm  Pitchingmoment coefficients, which are defined positive for a noseup rotation.  alpha , mach , build 
cn  Normalforce coefficients, which are defined positive for a normal force in the +Z direction.  alpha , mach , build 
ca  Axialforce coefficients, which are defined positive for a normal force in the +X direction.  alpha , mach , build 
caZeroBase  Axialforce coefficient with no base drag included.  alpha , mach , build 
caFullBase  Axialforce coefficient with full base drag included.  alpha , mach , build 
xcp  Distance from nose to center of pressure.  alpha , mach , build 
cna  Derivatives of normalforce coefficients relative to alpha .  alpha , mach , build 
cma  Derivatives of pitchingmoment coefficients relative to alpha .
 alpha , mach , build 
cyb  Derivatives of sideforce coefficients relative to sideslip angle.  alpha , mach , build 
cnb  Derivatives of yawingmoment coefficients relative to sideslip angle.  alpha , mach , build 
clb  Derivatives of rollingmoment coefficients relative to sideslip angle.  alpha , mach , build 
clod  Ratios of lift coefficient to drag coefficient.  alpha , mach , build 
cy  Sideforce coefficient.  alpha , mach , build 
cln  Yawingmoment coefficient.  alpha , mach , build 
cll  Rollingmoment coefficient.  alpha , mach , build 
Dynamic Derivative Fields for the 2008, 2011, and 2014 Version (File Type 42)
Field  Matrix of...  Function of... 

cnq  Normalforce derivatives due to pitch rate.  alpha , mach , alt , build 
cmq  Pitchingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
caq  Axialforce derivatives due to pitch rate.  alpha , mach , alt , build 
cnad  Normalforce derivatives due to rate of angle of attack.  alpha , mach , alt , build 
cmad  Pitchingmoment derivatives due to rate of angle of attack.  alpha , mach , alt , build 
cyq  Lateralforce derivatives due to pitch rate.  alpha , mach , alt , build 
clnq  Yawingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
cllq  Rollingmoment derivatives due to pitch rate.  alpha , mach , alt , build 
cyr  Sideforce derivatives due to yaw rate.  alpha , mach , alt , build 
clnr  Yawingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
cllr  Rollingmoment derivatives due to yaw rate.  alpha , mach , alt , build 
cyp  Lateralforce derivatives due to roll rate.  alpha , mach , alt , build 
clnp  Yawingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cllp  Rollingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cnp  Normalforce derivatives due to roll rate.  alpha , mach , alt , build 
cmp  Pitchingmoment derivatives due to roll rate.  alpha , mach , alt , build 
cap  Axialforce derivatives due to roll rate.  alpha , mach , alt , build 
cnr  Normalforce derivatives due to yaw rate.  alpha , mach , alt , build 
cmr  Pitchingmoment derivatives due to roll rate.  alpha , mach , alt , build 
car  Axialforce derivatives due to yaw rate.  alpha , mach , alt , build 
Read the 1976 version Digital DATCOM output file astdatcom.out
:
aero = datcomimport('astdatcom.out')
Read the 1976 Digital DATCOM output file astdatcom.out
using
zeros to replace data points where no DATCOM methods exist and displaying
status information in the MATLAB Command Window:
usenan = false; aero = datcomimport('astdatcom.out', usenan, 1 )
For more information on creating the digital DATCOM structure, see Importing from USAF Digital DATCOM Files. This example shows how to bring United States Air Force (USAF) Digital DATCOM files into the MATLAB environment.
The operational limitations of the 1976 version DATCOM apply to the data contained in AERO. For more information on DATCOM limitations, see [1], section 2.4.5.
USAF Digital DATCOM data for wing section, horizontal tail section, vertical tail section, and ventral fin section are not read.
1. AFFDLTR793032: The USAF Stability and Control DATCOM, Volume 1, User's Manual
2. AFRLVAWPTR19983009: MISSILE DATCOM, User's Manual – 1997 FORTRAN 90 Revision
3. AFRLRBWPTR20093015: MISSILE DATCOM, User's Manual – 2008 Revision
4. AFRLRBWPTR20113071: MISSILE DATCOM, User's Manual – 2011 Revision
5. AFRLRQWPTR20143999: MISSILE DATCOM, Users Manual – 2014 Revision