Aero input and outputs: Difference between revisions
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Properties aerodynamic functions in JSBSim can read and output. | |||
== Function inputs == | |||
Location of the aerodynamic reference point in the aircraft structural | Location of the aerodynamic reference point in the aircraft structural | ||
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/fdm/jsbsim/aero/ci2vel | /fdm/jsbsim/aero/ci2vel | ||
== Function outputs == | |||
Ground effect factors for lift and drag: | Ground effect factors for lift and drag: | ||
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Runtime-created aerodynamic force and moment components from definitions in | Runtime-created aerodynamic force and moment components from definitions in | ||
the <aerodynamics> section of the configuration file (varies per-aircraft): | the <aerodynamics> section of the configuration file (varies per-aircraft): | ||
Lift coefficients: | |||
/fdm/jsbsim/aero/coefficient/CLwbh | /fdm/jsbsim/aero/coefficient/CLwbh | ||
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/fdm/jsbsim/aero/coefficient/CLadot | /fdm/jsbsim/aero/coefficient/CLadot | ||
/fdm/jsbsim/aero/coefficient/CLq | /fdm/jsbsim/aero/coefficient/CLq | ||
Drag coefficients: | |||
/fdm/jsbsim/aero/coefficient/CDo | /fdm/jsbsim/aero/coefficient/CDo | ||
/fdm/jsbsim/aero/coefficient/CDDf | /fdm/jsbsim/aero/coefficient/CDDf | ||
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/fdm/jsbsim/aero/coefficient/CDDe | /fdm/jsbsim/aero/coefficient/CDDe | ||
/fdm/jsbsim/aero/coefficient/CDbeta | /fdm/jsbsim/aero/coefficient/CDbeta | ||
Side force coefficients: | |||
/fdm/jsbsim/aero/coefficient/CYb | /fdm/jsbsim/aero/coefficient/CYb | ||
/fdm/jsbsim/aero/coefficient/CYda | /fdm/jsbsim/aero/coefficient/CYda | ||
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/fdm/jsbsim/aero/coefficient/CYp | /fdm/jsbsim/aero/coefficient/CYp | ||
/fdm/jsbsim/aero/coefficient/CYr | /fdm/jsbsim/aero/coefficient/CYr | ||
Roll moment coefficients: | |||
/fdm/jsbsim/aero/coefficient/Clb | /fdm/jsbsim/aero/coefficient/Clb | ||
/fdm/jsbsim/aero/coefficient/Clp | /fdm/jsbsim/aero/coefficient/Clp | ||
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/fdm/jsbsim/aero/coefficient/Clda | /fdm/jsbsim/aero/coefficient/Clda | ||
/fdm/jsbsim/aero/coefficient/Cldr | /fdm/jsbsim/aero/coefficient/Cldr | ||
Pitch moment coefficients: | |||
/fdm/jsbsim/aero/coefficient/Cmalpha | /fdm/jsbsim/aero/coefficient/Cmalpha | ||
/fdm/jsbsim/aero/coefficient/CmDf | /fdm/jsbsim/aero/coefficient/CmDf | ||
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/fdm/jsbsim/aero/coefficient/Cmo | /fdm/jsbsim/aero/coefficient/Cmo | ||
/fdm/jsbsim/aero/coefficient/Cmde | /fdm/jsbsim/aero/coefficient/Cmde | ||
Yaw moment coefficients: | |||
/fdm/jsbsim/aero/coefficient/Cnb | /fdm/jsbsim/aero/coefficient/Cnb | ||
/fdm/jsbsim/aero/coefficient/Cnp | /fdm/jsbsim/aero/coefficient/Cnp | ||
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/fdm/jsbsim/aero/qbar-area | /fdm/jsbsim/aero/qbar-area | ||
{{JSBSim}} |
Revision as of 15:01, 6 March 2013
Properties aerodynamic functions in JSBSim can read and output.
Function inputs
Location of the aerodynamic reference point in the aircraft structural frame, measured in inches:
/fdm/jsbsim/metrics/aero-rp-x-in /fdm/jsbsim/metrics/aero-rp-y-in /fdm/jsbsim/metrics/aero-rp-z-in
Maximum and minimum alpha (angle of attack) in degrees:
/fdm/jsbsim/aero/alpha-max-deg /fdm/jsbsim/aero/alpha-min-deg
Wing span/(2*Velocity)
/fdm/jsbsim/aero/bi2vel
Wing chord/(2*Velocity)
/fdm/jsbsim/aero/ci2vel
Function outputs
Ground effect factors for lift and drag:
/fdm/jsbsim/aero/function/ground-effect-factor-lift /fdm/jsbsim/aero/function/ground-effect-factor-drag
Runtime-created aerodynamic force and moment components from definitions in the <aerodynamics> section of the configuration file (varies per-aircraft):
Lift coefficients:
/fdm/jsbsim/aero/coefficient/CLwbh /fdm/jsbsim/aero/coefficient/CLDf /fdm/jsbsim/aero/coefficient/CLDe /fdm/jsbsim/aero/coefficient/CLadot /fdm/jsbsim/aero/coefficient/CLq
Drag coefficients:
/fdm/jsbsim/aero/coefficient/CDo /fdm/jsbsim/aero/coefficient/CDDf /fdm/jsbsim/aero/coefficient/CDwbh /fdm/jsbsim/aero/coefficient/CDDe /fdm/jsbsim/aero/coefficient/CDbeta
Side force coefficients:
/fdm/jsbsim/aero/coefficient/CYb /fdm/jsbsim/aero/coefficient/CYda /fdm/jsbsim/aero/coefficient/CYdr /fdm/jsbsim/aero/coefficient/CYp /fdm/jsbsim/aero/coefficient/CYr
Roll moment coefficients:
/fdm/jsbsim/aero/coefficient/Clb /fdm/jsbsim/aero/coefficient/Clp /fdm/jsbsim/aero/coefficient/Clr /fdm/jsbsim/aero/coefficient/Clda /fdm/jsbsim/aero/coefficient/Cldr
Pitch moment coefficients:
/fdm/jsbsim/aero/coefficient/Cmalpha /fdm/jsbsim/aero/coefficient/CmDf /fdm/jsbsim/aero/coefficient/Cmq /fdm/jsbsim/aero/coefficient/Cmadot /fdm/jsbsim/aero/coefficient/Cmo /fdm/jsbsim/aero/coefficient/Cmde
Yaw moment coefficients:
/fdm/jsbsim/aero/coefficient/Cnb /fdm/jsbsim/aero/coefficient/Cnp /fdm/jsbsim/aero/coefficient/Cnr /fdm/jsbsim/aero/coefficient/Cnda /fdm/jsbsim/aero/coefficient/Cndr
Alpha of the wing in radians (includes the angle of incidence of the wing, if input):
/fdm/jsbsim/aero/alpha-wing-rad
Stall hysteresis, normalized:
/fdm/jsbsim/aero/stall-hyst-norm
Angles of attack and sideslip in radians and degrees (and the magnitudes):
/fdm/jsbsim/aero/alpha-rad /fdm/jsbsim/aero/beta-rad /fdm/jsbsim/aero/mag-beta-rad /fdm/jsbsim/aero/alpha-deg /fdm/jsbsim/aero/beta-deg /fdm/jsbsim/aero/mag-beta-deg
Dynamic pressure in psf:
/fdm/jsbsim/aero/qbar-psf
Dynamic pressure in the body axis XZ plane:
/fdm/jsbsim/aero/qbarUW-psf
Dynamic pressure in the body axis XY plane:
/fdm/jsbsim/aero/qbarUV-psf
Time rate of change in alpha and sideslip in deg/sec and rad/sec:
/fdm/jsbsim/aero/alphadot-rad_sec /fdm/jsbsim/aero/betadot-rad_sec /fdm/jsbsim/aero/alphadot-deg_sec /fdm/jsbsim/aero/betadot-deg_sec
Altitude of CG divided by wing span:
/fdm/jsbsim/aero/h_b-cg-ft
Altitude of MAC divided by wing span:
/fdm/jsbsim/aero/h_b-mac-ft
Aerodynamic rotational rates in rad/sec (includes wind effects, if any):
/fdm/jsbsim/velocities/p-aero-rad_sec /fdm/jsbsim/velocities/q-aero-rad_sec /fdm/jsbsim/velocities/r-aero-rad_sec
Aerodynamic velocities in ft/sec (includes wind effects, if any):
/fdm/jsbsim/velocities/u-aero-fps /fdm/jsbsim/velocities/v-aero-fps /fdm/jsbsim/velocities/w-aero-fps
The body axis aerodynamic force vector of the aircraft in lbs:
/fdm/jsbsim/forces/fbx-aero-lbs /fdm/jsbsim/forces/fby-aero-lbs /fdm/jsbsim/forces/fbz-aero-lbs
The stability axis aerodynamic force vector of the aircraft in lbs:
/fdm/jsbsim/forces/fwx-aero-lbs /fdm/jsbsim/forces/fwy-aero-lbs /fdm/jsbsim/forces/fwz-aero-lbs
The body axis aerodynamic moment vector of the aircraft in ft-lbs:
/fdm/jsbsim/moments/l-aero-lbsft /fdm/jsbsim/moments/m-aero-lbsft /fdm/jsbsim/moments/n-aero-lbsft
The lift coefficient squared:
/fdm/jsbsim/aero/cl-squared
Dynamic pressure times reference area:
/fdm/jsbsim/aero/qbar-area