Bring DATCOM file into MATLAB environment
Read the 1976 version Digital DATCOM output file
astdatcom.out
.
aero = datcomimport('astdatcom.out')
aero = 1×1 cell array {1×1 struct}
Read the 1976 Digital DATCOM output file
astdatcom.out
using zeros to replace data points where no DATCOM
methods exist. Use usenanvar variable to set
usenan
argument to false
.
usenanvar = false;
aero = datcomimport('astdatcom.out',usenanvar)
aero = 1×1 cell array {1×1 struct}
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. Use usenanvar variable to set
usenan
argument to false
.
usenanvar = false;
aero = datcomimport('astdatcom.out',usenanvar,1)
Loading file 'astdatcom.out'. Reading input data from file 'astdatcom.out'. Reading output data from file 'astdatcom.out'. aero = 1×1 cell array {1×1 struct}
Read the 1976 Digital DATCOM output file
astdatcom.out
using NaNs to replace data points where no DATCOM
methods exist, displaying status information in the MATLAB Command Window, and specifying the DATCOM output file type. Use
usenanvar variable to set usenan
argument to
true
.
usenanvar = true;
aero = datcomimport('astdatcom.out',usenanvar,1,6)
Loading file 'astdatcom.out'. Reading input data from file 'astdatcom.out'. Reading output data from file 'astdatcom.out'. aero = 1×1 cell array {1×1 struct}
file
— DATCOM file Digital DATCOM output file name, specified as a character vector or cell array of file names. This file is generated from USAF Digital DATCOM files.
The datcomimport
supports only these USAF Digital DATCOM files.
You can rename the output files before importing them.
Output File from DATCOM  File Type Versions 

 1976, 1999, 2007, 2008, 2011, and 2014 
 2007, 2008, 2011, and 2014 
 2008, 2011, and 2014 
Example: for006.dat
The datcomimport
function accepts DATCOM files of the type
specified by the filetype
argument. By default, the file type is
6 ( for006.dat
, output by all DATCOM versions).
Data Types: char
 string
usenan
— Replace data pointstrue
(default)  false
While importing the DATCOM file, replace data points with NaNs
(true
) or zeroes (false
) where no DATCOM methods
exist or where methods are not applicable.
Data Types: char
 string
verbose
— Read status2
(default)  0
 1
Read status of import of DATCOM file, specified as:
0
— No status information.
1
— Display a status information as a progress bar.
2
— Display status information in the MATLAB Command Window.
Data Types: double
filetype
— DATCOM file type6
(default)  21
42
DATCOM file type, specified as 6
, 21
, or
42
.
Depending on the file type, the datcomimport
function expects
the imported DATCOM files to contain the fields listed in the Expected
Fields column.
filetype  Output File from DATCOM  File Type Versions  Expected Fields 

6

 1976, 1999, 2007, 2008, 2011, and 2014  
21 
 2007, 2008, 2011, and 2014  
42 
 2008, 2011, and 2014 
If filetype
is 21
, the function collates the
breakpoints and data from all the cases and appends them as the last entry of
aero
.
Data Types: double
aero
— DATCOM structuresDATCOM structures, returned as a cell array of structures.
The operational limitations of the 1976 version DATCOM apply to the data contained in AERO. For more information on DATCOM limitations, see References, section 2.4.5.
USAF Digital DATCOM data for wing section, horizontal tail section, vertical tail section, and ventral fin section are not read.
1976 version of file type 6 DATCOM files must contain these fields.
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. 
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

1999 version of file type 6 DATCOM files must contain these fields.
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 
2007, 2008, 2011, and 2014 versions of file type 6 DATCOM files must contain these fields.
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 
2007, 2008, 2011, and 2014 versions of file type 21 DATCOM files must contain these fields.
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 
2008, 2011, and 2014 versions of file type 42 DATCOM files must contain these fields.
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 
[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
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