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datcomimport

Bring DATCOM file intoMATLABenvironment

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Syntax

aero = datcomimport(file)
aero = datcomimport(file,usenan)
aero = datcomimport(file,usenan,verbose)
aero = datcomimport(file,usenan,verbose,filetype)

Description

example

aero= datcomimport(file)imports aerodynamic data fromfileintoaero. Before reading the United States Air Force Digital DATCOM file,datcomimportinitializes values to 99999 when there is not a full set of data for the DATCOM case.

example

aero= datcomimport(file,usenan)replaces data points with NaN or zero where no DATCOM methods exist or where the method is not applicable.

example

aero= datcomimport(file,usenan,verbose)displays the status of the DATCOM file being read in the MATLAB®Command Window.

example

aero= datcomimport(file,usenan,verbose,filetype)imports a DATCOM of a particular USAF Digital DATCOM file type.

Examples

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Read the 1976 version Digital DATCOM output fileastdatcom.out.

aero = datcomimport(“astdatcom.out”)
aero = 1×1 cell array {1×1 struct}

Read the 1976 Digital DATCOM output fileastdatcom.outusing zeros to replace data points where no DATCOM methods exist. Useusenanvarvariable to setusenanargument tofalse.

usenanvar = false; aero = datcomimport(“astdatcom.out”,usenanvar)
aero = 1×1 cell array {1×1 struct}

Read the 1976 Digital DATCOM output fileastdatcom.outusing zeros to replace data points where no DATCOM methods exist and displaying status information in the MATLAB Command Window. Useusenanvarvariable to setusenanargument tofalse.

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 fileastdatcom.outusing 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. Useusenanvarvariable to setusenanargument totrue.

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}

Input Arguments

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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.

Thedatcomimportsupports only these USAF Digital DATCOM files. You can rename the output files before importing them.

Output File from DATCOM File Type Versions

for006.datby all DATCOM versions

1976, 1999, 2007, 2008, 2011, and 2014

for021.datby DATCOM 2007, DATCOM 2008, DATCOM 2011, and DATCOM 2014

2007, 2008, 2011, and 2014

for042.csvby DATCOM 2008, DATCOM 2011, and DATCOM 2014

2008, 2011, and 2014

Example:for006.dat

Dependencies

Thedatcomimportfunction accepts DATCOM files of the type specified by thefiletypeargument. By default, the file type is 6 (for006.dat, output by all DATCOM versions).

Data Types:char|string

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

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

DATCOM file type, specified as6,21, or42.

Depending on the file type, thedatcomimportfunction expects the imported DATCOM files to contain the fields listed in theExpected Fieldscolumn.

filetype Output File from DATCOM File Type Versions Expected Fields
6

for006.datby all DATCOM versions

1976, 1999, 2007, 2008, 2011, and 2014
21

for021.datby DATCOM 2007, DATCOM 2008, DATCOM 2011, and DATCOM 2014

2007, 2008, 2011, and 2014
42

for042.csvby DATCOM 2008, DATCOM 2011, and DATCOM 2014

2008, 2011, and 2014

Note

Iffiletypeis21, the function collates the breakpoints and data from all the cases and appends them as the last entry ofaero.

Data Types:double

Output Arguments

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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, seeReferences, 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

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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 数量的海拔。 0
nalpha Number of angles of attack. 0
rnnub Array of Reynolds numbers. []
hypers Logical denoting, whentrue, thatmachnumbers abovetsmachare hypersonic. Default values are supersonic. false
loop 标量表示loopin的类型g done to generate the DATCOM file. Whenloopis1,machandaltare varied together. Whenloopis2,machvaries whilealtis fixed. Altitude is then updated and Mach numbers are cycled through again. Whenloopis3,machis fixed whilealtvaries.machis 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 totrue. false
damp Logical denoting the reading of dynamic derivative data for the case. When dynamic derivative runs are read, this value is set totrue. 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 totrue. 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 totrue. 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 totrue. 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 totrue. 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 totrue. 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 totrue. 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 totrue. false
pwr Logical denoting the reading of power effects data for the case. When power effects runs are read, this value is set totrue. false
grnd Logical denoting the reading of ground effects data for the case. When ground effects runs are read, this value is set totrue. 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 数量的控制表面变形量:delta,deltal, ordeltar. 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 标量表示地面海拔的数量。 0
grndht Array of ground heights. []
config Structure of logicals denoting whether the case contains horizontal tails.

false, as follows.

config.downwash = false; config.body = false; config.wing = false; config.htail = false; config.vtail = false; config.vfin = false;
version Version of DATCOM file. 1976

Static Longitude and Lateral Stability Fields Available for the 1976 Version (File Type 6)

Field Matrix of... Function of...
cd Drag coefficients, which are defined positive for an 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 πtching-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 toalpha. alpha,mach,alt,build,grndht,delta
cma Derivatives of pitching-moment coefficients relative toalpha. 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 d的比率ynamic 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 πtching-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 πtching-moment derivatives due to rate of angle of attack. alpha,mach,alt,build
clp 由于滚转角速度滚动力矩衍生品。 alpha,mach,alt,build
cyp Lateral-force derivatives due to roll rate. alpha,mach,alt,build
cnp 由于滚转率偏荡的衍生品。 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, andalt, oralpha,delta,mach, andaltfor 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, andalt, oralpha,delta,mach, andaltfor 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 阻力系数的t 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 forhypers = true)
zcg_b Vertical locations of the center of gravity. mach,alt, number of runs (normally 1, 2 forhypers = true)
basearea_b Body base area. mach,alt, number of runs (normally 1, 2 forhypers = true)
cd0_b Body zero lift drags. mach,alt, number of runs (normally 1, 2 forhypers = true)
basedrag_b Body base drags. mach,alt, number of runs (normally 1, 2 forhypers = true)
fricdrag_b Body friction drags. mach,alt, number of runs (normally 1, 2 forhypers = true)
presdrag_b Body pressure drags. mach,alt, number of runs (normally 1, 2 forhypers = 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 /γ mach,alt
cmothetaw (cmo/theta)w mach,alt
cmothetah (cmo/theta)h mach,alt
espeff (epsoln)eff alpha,mach, andalt
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 eitherwb(wing-body) orbht(body-horizontal tail). mach,alt.
cnam14_**** (cna)m=1.4, where****is eitherwb(wing-body) orbht(body-horizontal tail). mach,alt
area_*_** Areas, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
taperratio_*_** Taper ratios, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
aspectratio_*_** Aspect ratios, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
qcsweep_*_** Quarter chord sweeps, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
mac_*_** Mean aerodynamic chords, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
qcmac_*_** Quarter chordx(mac), where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
ymac_*_** y(mac), where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
cd0_*_** Zero lift drags, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
friccoeff_*_** Friction coefficients, where*is eitherw(wing),ht(horizontal tail),vt(vertical tail), orvf(ventral fin) and**is eithertt(total theoretical),ti(theoretical inboard),te(total exposed),ei(exposed inboard), oro(outboard). mach,alt, number of runs (normally 1, 2 forhypers = true)
cla_b_*** cla-b(***), where***is eitherw(wing) orht(stabilizer). mach,alt, number of runs (normally 1, 2 forhypers = true)
cla_***_b cla-***(b), where***is eitherw(wing) orht(stabilizer). mach,alt, number of runs (normally 1, 2 forhypers = true)
k_b_*** k-b(***), where***is eitherw(wing) orht(stabilizer). mach,alt, number of runs (normally 1, 2 forhypers = true)
k_***_b k-***(b), where***is eitherw(wing) orht(stabilizer). mach,alt, number of runs (normally 1, 2 forhypers = true)
xacc_b_*** xac/c-b(***), where***is eitherw(wing) orht(stabilizer). mach,alt, number of runs (normally 1, 2 forhypers = true)
cdlcl2_*** cdl/cl^2, where***is eitherw(wing) orht(stabilizer). mach,alt
clbcl_*** clb/cl, where***is eitherw(wing) orht(stabilizer). mach,alt
fmach0_*** Force break Mach numbers with zero sweep, where***is eitherw(wing) orht(stabilizer). mach,alt
fmach_*** Force break Mach numbers with sweep, where***is eitherw(wing) orht(stabilizer). mach,alt
macha_*** mach(a), where***is eitherw(wing) orht(stabilizer). mach,alt
machb_*** mach(b), where***is eitherw(wing) orht(stabilizer). mach,alt
claa_*** cla(a), where***is eitherw(wing) orht(stabilizer). mach,alt
clab_*** cla(b), where***is eitherw(wing) orht(stabilizer). mach,alt
clbm06_*** (clb/cl)m=0.6, where***is eitherw(wing) orht(stabilizer). mach,alt
clbm14_*** (clb/cl)m=1.4, where***is eitherw(wing) orht(stabilizer). mach,alt
clalpmach_*** Five Mach numbers for the lift curve slope, where***is eitherw(wing) orht(stabilizer). index,mach,alt
clalp_*** Five lift-curve slope values, where***is eitherw(wing) orht(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 数量的海拔。 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 标量表示loopin的类型g performed to generate the DATCOM file. Whenloopis1,machandaltare varied together. The only loop option for the 1999 version of DATCOM isloopis equal to1. 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 totrue. false
damp Logical denoting the reading of dynamic derivative data for the case. When dynamic derivative runs are read, this value is set totrue. 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 totrue. false
hypeff Logical denoting the reading of hypersonic data for the case. When hypersonic data is read, this value is set totrue. false
ngh 标量表示地面海拔的数量。 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 πtching-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 toalpha. alpha,mach,alt,build
cma Derivatives of pitching-moment coefficients relative toalpha. 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 πtching-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 πtching-moment derivatives due to rate of angle of attack. alpha,mach,alt,build
clp 由于滚转角速度滚动力矩衍生品。 alpha,mach,alt,build
cyp Lateral force derivatives due to roll rate. alpha,mach,alt,build
cnp 由于滚转率偏荡的衍生品。 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 数量的海拔。 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 标量表示loopin的类型g performed to generate the DATCOM file. Whenloopis1,machandaltare varied together. The only loop option for the 2007 version of DATCOM isloop, equal to1. 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 totrue. false
damp Logical denoting the reading of dynamic derivative data for the case. When dynamic derivative runs are read, this value is set totrue. 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 totrue. false
hypeff Logical denoting the reading of hypersonic data for the case. When hypersonic data is read, this value is set totrue. false
ngh 标量表示地面海拔的数量。 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 πtching-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 toalpha. alpha,mach,alt,build
cma Derivatives of pitching-moment coefficients relative toalpha. 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 πtching-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 πtching-moment derivatives due to rate of angle of attack. alpha,mach,alt,build
clp 由于滚转角速度滚动力矩衍生品。 alpha,mach,alt,build
cyp Lateral-force derivatives due to roll rate. alpha,mach,alt,build
cnp 由于滚转率偏荡的衍生品。 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 标量表示loopin的类型g performed to generate the DATCOM file. Whenloopis 1,machandaltare varied together. The only loop option for the 2007, 2008, 2011, and 2014 versions of DATCOM isloopequal to1. []
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 πtching-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 πtching-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 πtching-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 由于滚转率偏荡的衍生品。 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 totrue. false
damp Logical denoting the reading of dynamic derivative data for the case. When dynamic derivative runs are read, this value is set totrue. 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 totrue. 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 πtching-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 toalpha. alpha,mach,build
cma Derivatives of pitching-moment coefficients relative toalpha. 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 πtching-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 πtching-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 由于滚转率偏荡的衍生品。 alpha,mach,alt,build
cllp 由于滚转角速度滚动力矩衍生品。 alpha,mach,alt,build
cnp Normal-force derivatives due to roll rate. alpha,mach,alt,build
cmp πtching-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 πtching-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

Topics