| Aerospace Toolbox | |
aero = datcomimport(file)
aero = datcomimport(file, usenan)
aero = datcomimport(file, usenan, verbose)
aero = datcomimport(file) takes a filename as a string, or a cell array of filenames as strings, file, and imports aerodynamic data from file into a cell array of structures, aero. Prior to reading DATCOM file, values are initialized to 99999, in order to show when there is not a full set of data for the DATCOM case.
aero = datcomimport(file, usenan) is an alternate method allowing using NaN or zero to replace data points where no DATCOM methods exist or where the method is not applicable. The default value for usenan is true.
aero = datcomimport(file, usenan, verbose) is an alternate method allowing additional specification of how the status of the DATCOM file being read is displayed. The default value for verbose is 2, which displays a wait bar. Other options are 0, which displays no information, and 1, which displays text to the MATLAB Command window.
Fields for the 1976 and 1999 versions of the file are described in the following:
The fields of aero depend on the data within the DATCOM file. Common fields for the 1976 version are the following:
| Field | Description | Default |
|---|---|---|
| case | String 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 | String denoting the specified system of units for the case. | 'ft' |
| deriv | String 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. | false, as follows.config.downwash = false; config.body = false; config.wing = false; config.htail = false; config.vtail = false; config.vfin = false; |
Static longitude and lateral stability fields available for the 1976 version are:
| 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 with respect to alpha. | alpha, mach, alt, build, grndht, delta |
| cma | Derivatives of pitching-moment coefficients with respect to alpha. | alpha, mach, alt, build, grndht, delta |
| cyb | Derivatives of side-force coefficients with respect to sideslip angle. | alpha, mach, alt, build, grndht, delta |
| cnb | Derivatives of yawing-moment coefficients with respect to sideslip angle. | alpha, mach, alt, build, grndht, delta |
| clb | Derivatives of rolling-moment coefficients with respect 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 with respect to angle of attack. | alpha, mach, alt, build, grndht, delta |
Dynamic derivative fields for the 1976 version are:
| Field | Matrix of... | Function of... |
|---|---|---|
| clq | Rolling-moment 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 are:
| 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, will 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 will 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 are:
| 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 are:
| 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 are:
| 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 are:
| 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 strings 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 are:
| 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 are:
| 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 |
Common fields for the 1999 version are the following:
| Field | Description | Default |
|---|---|---|
| case | String 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 version 1999 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 | String denoting the specified system of units for the case. | 'ft' |
| deriv | String 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. | As follows: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 = []; |
Static longitude and lateral stability fields available for the 1999 version are:
| 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 with respect to alpha. | alpha, mach, alt, build |
| cma | Derivatives of pitching-moment coefficients with respect to alpha. | alpha, mach, alt, build |
| cyb | Derivatives of side-force coefficients with respect to sideslip angle. | alpha, mach, alt, build |
| cnb | Derivatives of yawing-moment coefficients with respect to sideslip angle. | alpha, mach, alt, build |
| clb | Derivatives of rolling-moment coefficients with respect 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 are:
| 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 |
Read the 1976 version Digital DATCOM output file astdatcom.out:
aero = datcomimport('astdatcom.out')
Read the 1976 Digital DATCOM output file astdatcom.out using zeros to replace data points where no DATCOM methods exist and displaying status information in the MATLAB Command window:
usenan = false;
aero = datcomimport('astdatcom.out', usenan, 1 )
The operational limitations of the 1976 version DATCOM apply to the data contained in AERO. For more information on DATCOM limitations, see [1], section 2.4.5.
USAF Digital DATCOM data for wing section, horizontal tail section, vertical tail section and ventral fin section are not read.
1. AFFDL-TR-79-3032: The USAF Stability and Control DATCOM, Volume 1, Users Manual
2. AFRL-VA-WP-TR-1998-3009: MISSILE DATCOM, Users Manual – 1997 FORTRAN 90 Revision
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