Main Content
datcomimport
Bring DATCOM file into MATLAB environment
Syntax
Description
Examples
Read Digital DATCOM Files
These examples show how to read diginal DATACOM files.
Read 1976 Version of Digital DATCOM File
Read the 1976 version Digital DATCOM output file astdatcom.out.
aero = datcomimport('astdatcom.out')aero = 1x1 cell array
{1x1 struct}
Read USAF Digital DATCOM Output File Replacing Data Points with Zeroes
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 = 1x1 cell array
{1x1 struct}
Read USAF Digital DATCOM Output File Replacing Data Points with Zeroes Specifying Verbose Settings
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 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 = 1x1 cell array
{1x1 struct}
Read USAF Digital DATCOM Output File Replacing Data Points with Zeroes and Specifying Verbose Settings and DATCOM File Type
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 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 = 1x1 cell array
{1x1 struct}
Input Arguments
file — DATCOM file
character vector | cell array of file names
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
Dependencies
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 points
true (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 status
2 (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 type
6 (default) | 2142
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 |
Note
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
Output Arguments
aero — DATCOM structures
cell array of structures
DATCOM structures, returned as a cell array of structures.
Limitations
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.
More About
Fields for 1976 Version (File Type 6)
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 high-lift 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 high-lift 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 high-lift data for the case.
When control/trim tab runs are read, this value is set to true. | false |
tjet | Logical denoting the reading of transverse-jet control data for the case. When
transverse-jet 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 semi-span theoretical panel for wing. This value is used to determine if the configuration contains a canard. | 1 |
hsspn | Scalar denoting the semi-span 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 control-surface streamwise deflection angles. | [] |
deltal | Array of left lifting surface streamwise control deflection angles, which are defined positive for trailing-edge down. | [] |
deltar | Array of right lifting surface streamwise control deflection angles, which are defined positive for trailing-edge 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 aft-acting load. | alpha, mach, alt,
build, grndht,
delta |
cl | Lift coefficients, which are defined positive for an up-acting load. | alpha, mach, alt,
build, grndht, delta
|
cm | Pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach, alt,
build, grndht,
delta |
cn | Normal-force coefficients, which are defined positive for a normal force in the +Z direction. | alpha, mach, alt,
build, grndht,
delta |
ca | Axial-force 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 pitching-moment coefficients relative to
alpha. | alpha, mach, alt,
build, grndht,
delta |
cyb | Derivatives of side-force coefficients relative to sideslip angle. | alpha, mach, alt,
build, grndht,
delta |
cnb | Derivatives of yawing-moment coefficients relative to sideslip angle. | alpha, mach, alt,
build, grndht,
delta |
clb | Derivatives of rolling-moment 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 | Pitching-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
clad | Lift-force derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
cmad | Pitching-moment derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
clp | Rolling-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cyp | Lateral-force derivatives due to roll rate. | alpha, mach, alt,
build |
cnp | Yawing-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cnr | Yawing-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
clr | Rolling-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
High-Lift 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 linear-lift angle of attack range. | delta, mach,
alt |
dcm_sym | Incremental pitching-moment coefficients due to deflection of control surface, valid in the linear-lift 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 | Lift-curve slope of the deflected, translated surface. | delta, mach,
alt |
cha_sym | Control-surface hinge-moment derivatives due to angle of attack. These derivatives, when defined positive, tend to rotate the flap trailing edge down. | delta, mach,
alt |
chd_sym | Control-surface hinge-moment 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 |
High-Lift 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 spoiler-slot-deflector control. | delta, mach,
alt |
dsc | Projected height of spoiler control. | delta, mach,
alt |
clroll | Incremental rolling-moment 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 yawing-moment 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 |
High-Lift 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 | Flap-hinge moment coefficients tab free. | alpha, delta, mach,
alt
|
fhmcoeff_lock | Flap-hinge moment coefficients tab locked. | alpha, delta, mach,
alt |
fhmcoeff_gear | Flap-hinge moment coefficients due to gearing. | alpha, delta, mach,
alt
|
ttab_def | Trim-tab deflections for zero stick force. | alpha, delta, mach,
alt
|
High-Lift 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 up-acting load. | alpha, mach,
alt |
cd_utrim | Untrimmed drag coefficients, which are defined positive for an aft-acting load. | alpha, mach,
alt |
cm_utrim | Untrimmed pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach,
alt |
delt_trim | Trimmed control-surface streamwise deflection angles. | alpha, mach,
alt |
dcl_trim | Trimmed incremental lift coefficients in the linear-lift 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 control-surface hinge-moment derivatives due to angle of attack. | alpha, mach,
alt |
chd_trim | Trimmed control-surface hinge-moment derivatives due to control deflection. | alpha, mach,
alt |
cl_tailutrim | Untrimmed stabilizer lift coefficients, which are defined positive for an up-acting load. | alpha, mach,
alt |
cd_tailutrim | Untrimmed stabilizer drag coefficients, which are defined positive for an aft-acting load. | alpha, mach,
alt |
cm_tailutrim | Untrimmed stabilizer pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach,
alt |
hm_tailutrim | Untrimmed stabilizer hinge-moment 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 up-acting load. | alpha, mach,
alt |
cd_tailtrim | Trimmed stabilizer drag coefficients, which are defined positive for an aft-acting load. | alpha, mach,
alt |
cm_tailtrim | Trimmed stabilizer pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach,
alt |
hm_tailtrim | Trimmed stabilizer hinge-moment 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 up-acting load. | alpha, mach,
alt |
cd_trimi | Drag coefficients at trim incidence. These coefficients are defined positive for an aft-acting 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 | iv-b(w) | alpha, mach, alt
|
hiv_w_h | iv-w(h) | alpha, mach, alt
|
hiv_b_h | iv-b(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 (wing-body) or bht (body-horizontal
tail). | mach, alt. |
cnam14_**** | (cna)m=1.4, where **** is either
wb (wing-body) or bht (body-horizontal
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_*** | cla-b(***), 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_*** | k-b(***), 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/c-b(***), 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 lift-curve slope values, where *** is either
w (wing) or ht (stabilizer). | index, mach, alt
|
Fields for 1999 Version (File Type 6)
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 lateral-direction 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 aft-acting load. | alpha, mach, alt,
build |
cl | Lift coefficients, which are defined positive for an up-acting load. | alpha, mach, alt,
build |
cm | Pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, machalt,
build |
cn | Normal-force coefficients, which are defined positive for a normal force in the +Z direction. | alpha, mach, alt,
build |
ca | Axial-force 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 normal-force coefficients relative to alpha. | alpha, mach, alt,
build |
cma | Derivatives of pitching-moment coefficients relative to
alpha. | alpha, mach, alt,
build |
cyb | Derivatives of side-force coefficients relative to sideslip angle. | alpha, mach, alt,
build |
cnb | Derivatives of yawing-moment coefficients relative to sideslip angle. | alpha, mach, alt,
build |
clb | Derivatives of rolling-moment coefficients relative to sideslip angle. | alpha, mach, alt,
build |
clod | Ratios of lift coefficient to drag coefficient. | alpha, mach, alt,
build |
cy | Side-force coefficients. | alpha, mach, alt,
build |
cln | Yawing-moment coefficient in body-axis. | alpha, mach, alt,
build |
cll | Rolling-moment coefficient in body-axis. | alpha, mach, alt,
build |
Dynamic Derivative Fields for the 1999 Version (File Type 6)
| Field | Matrix of... | Function of... |
|---|---|---|
cnq | Normal-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cmq | Pitching-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
caq | Axial-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cnad | Normal-force derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
cmad | Pitching-moment derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
clp | Rolling-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cyp | Lateral force derivatives due to roll rate. | alpha, mach, alt,
build |
cnp | Yawing-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cnr | Yawing-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
clr | Rolling-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
cyr | Side force derivatives due to yaw rate. | alpha, mach, alt,
build |
Fields for 2007, 2008, 2011, and 2014 Versions (File Type 6)
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. Note This 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 lateral-direction 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 lateral-direction 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 aft-acting load. | alpha, mach, alt,
build |
cl | Lift coefficients, which are defined positive for an up-acting load. | alpha, mach, alt,
build |
cm | Pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, machalt,
build |
cn | Normal-force coefficients, which are defined positive for a normal force in the +Z direction. | alpha, mach, alt,
build |
ca | Axial-force 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 normal-force coefficients relative to alpha. | alpha, mach, alt,
build |
cma | Derivatives of pitching-moment coefficients relative to
alpha. | alpha, mach, alt,
build |
cyb | Derivatives of side-force coefficients relative to sideslip angle. | alpha, mach, alt,
build |
cnb | Derivatives of yawing-moment coefficients relative to sideslip angle. | alpha, mach, alt,
build |
clb | Derivatives of rolling-moment coefficients relative to sideslip angle. | alpha, mach, alt,
build |
clod | Ratios of lift coefficient to drag coefficient. | alpha, mach, alt,
build |
cy | Side-force coefficients. | alpha, mach, alt,
build |
cln | Yawing-moment coefficient in body-axis. | alpha, mach, alt,
build |
cll | Rolling-moment coefficient in body-axis. | alpha, mach, alt,
build |
Dynamic Derivative Fields for the 2007, 2008, 2011, and 2014 Versions (File Type 6)
| Field | Matrix of... | Function of... |
|---|---|---|
cnq | Normal-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cmq | Pitching-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
caq | Axial-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cnad | Normal-force derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
cmad | Pitching-moment derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
clp | Rolling-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cyp | Lateral-force derivatives due to roll rate. | alpha, mach, alt,
build |
cnp | Yawing-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cnr | Yawing-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
clr | Rolling-moment derivatives due to yaw rate | alpha, mach, alt,
build |
cyr | Side-force derivatives due to yaw rate. | alpha, mach, alt,
build |
Fields for 2007, 2008, 2011, and 2014 Versions (File Type 21)
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. Note This 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 lateral-direction 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 | Normal-force 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 | Pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
ca | Axial-force 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 | Side-force coefficients. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cln | Yawing-moment coefficient in body-axis. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cll | Rolling-moment coefficient in body-axis. | 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 | Normal-force 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 | Pitching-moment 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 | Normal-force derivatives due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cmq | Pitching-moment derivatives due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
caq | Axial-force derivatives due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cyq | Side-force due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
clnq | Yawing-moment due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cllq | Rolling-moment due to pitch rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cnp | Yawing-moment derivatives due to roll rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cap | Axial-force due to roll rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cyp | Lateral-force derivatives due to roll rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
clnp | Yawing-moment due to roll rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cllp | Rolling-moment due to roll rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cnr | Yawing-moment derivatives due to yaw rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
car | Axial-force due to yaw rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cyr | Side-force derivatives due to yaw rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
clnr | Yawing-moment due to yaw rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
cllr | Rolling-moment due to yaw rate. | alpha, mach, alt,
beta, config.fin1.delta,
config.fin2.delta, config.fin3.delta,
config.fin4.delta |
Fields for 2008, 2011, and 2014 Version (File Type 42)
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. Note This 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 lateral-direction 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 aft-acting load. | alpha, mach,
build |
cl | Lift coefficients, which are defined positive for an up-acting load. | alpha, mach,
build |
cm | Pitching-moment coefficients, which are defined positive for a nose-up rotation. | alpha, mach,
build |
cn | Normal-force coefficients, which are defined positive for a normal force in the +Z direction. | alpha, mach,
build |
ca | Axial-force coefficients, which are defined positive for a normal force in the +X direction. | alpha, mach,
build |
caZeroBase | Axial-force coefficient with no base drag included. | alpha, mach,
build |
caFullBase | Axial-force coefficient with full base drag included. | alpha, mach,
build |
xcp | Distance from nose to center of pressure. | alpha, mach,
build |
cna | Derivatives of normal-force coefficients relative to
alpha. | alpha, mach,
build |
cma | Derivatives of pitching-moment coefficients relative to
alpha. | alpha, mach,
build |
cyb | Derivatives of side-force coefficients relative to sideslip angle. | alpha, mach,
build |
cnb | Derivatives of yawing-moment coefficients relative to sideslip angle. | alpha, mach,
build |
clb | Derivatives of rolling-moment coefficients relative to sideslip angle. | alpha, mach,
build |
clod | Ratios of lift coefficient to drag coefficient. | alpha, mach,
build |
cy | Side-force coefficient. | alpha, mach,
build |
cln | Yawing-moment coefficient. | alpha, mach,
build |
cll | Rolling-moment coefficient. | alpha, mach,
build |
Dynamic Derivative Fields for the 2008, 2011, and 2014 Version (File Type 42)
| Field | Matrix of... | Function of... |
|---|---|---|
cnq | Normal-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cmq | Pitching-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
caq | Axial-force derivatives due to pitch rate. | alpha, mach, alt,
build |
cnad | Normal-force derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
cmad | Pitching-moment derivatives due to rate of angle of attack. | alpha, mach, alt,
build |
cyq | Lateral-force derivatives due to pitch rate. | alpha, mach, alt,
build |
clnq | Yawing-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
cllq | Rolling-moment derivatives due to pitch rate. | alpha, mach, alt,
build |
cyr | Side-force derivatives due to yaw rate. | alpha, mach, alt,
build |
clnr | Yawing-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
cllr | Rolling-moment derivatives due to yaw rate. | alpha, mach, alt,
build |
cyp | Lateral-force derivatives due to roll rate. | alpha, mach, alt,
build |
clnp | Yawing-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cllp | Rolling-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cnp | Normal-force derivatives due to roll rate. | alpha, mach, alt,
build |
cmp | Pitching-moment derivatives due to roll rate. | alpha, mach, alt,
build |
cap | Axial-force derivatives due to roll rate. | alpha, mach, alt,
build |
cnr | Normal-force derivatives due to yaw rate. | alpha, mach, alt,
build |
cmr | Pitching-moment derivatives due to roll rate. | alpha, mach, alt,
build |
car | Axial-force derivatives due to yaw rate. | alpha, mach, alt,
build |
References
[1] AFFDL-TR-79-3032: The USAF Stability and Control DATCOM, Volume 1, User's Manual
[2] AFRL-VA-WP-TR-1998-3009: MISSILE DATCOM, User's Manual – 1997 FORTRAN 90 Revision
[3] AFRL-RB-WP-TR-2009-3015: MISSILE DATCOM, User's Manual – 2008 Revision
[4] AFRL-RB-WP-TR-2011-3071: MISSILE DATCOM, User's Manual – 2011 Revision
[5] AFRL-RQ-WP-TR-2014-3999: MISSILE DATCOM, Users Manual – 2014 Revision
Version History
Introduced in R2006b
See Also
MATLAB Command
You clicked a link that corresponds to this MATLAB command:
Run the command by entering it in the MATLAB Command Window. Web browsers do not support MATLAB commands.
Select a Web Site
Choose a web site to get translated content where available and see local events and offers. Based on your location, we recommend that you select: .
You can also select a web site from the following list
How to Get Best Site Performance
Select the China site (in Chinese or English) for best site performance. Other MathWorks country sites are not optimized for visits from your location.
Americas
- América Latina (Español)
- Canada (English)
- United States (English)
Europe
- Belgium (English)
- Denmark (English)
- Deutschland (Deutsch)
- España (Español)
- Finland (English)
- France (Français)
- Ireland (English)
- Italia (Italiano)
- Luxembourg (English)
- Netherlands (English)
- Norway (English)
- Österreich (Deutsch)
- Portugal (English)
- Sweden (English)
- Switzerland
- United Kingdom (English)
Asia Pacific
- Australia (English)
- India (English)
- New Zealand (English)
- 中国
- 日本Japanese (日本語)
- 한국Korean (한국어)