Interface | Description |
---|---|
Aero3DOF |
Interface in common to all 3-DOF static aerodynamics models.
|
ControlAero3DOF |
Interface in common to all 3-DOF static flight control aerodynamics models.
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ControlHingeMoments |
Interface in common to all aerodynamic flight control hinge-moment models.
|
Class | Description |
---|---|
Aero3DOFTabular |
A 3DOF aerodynamic model that makes use of data tabulated as a function of angle of
attack and Mach number.
|
Aero3DOFTabularGE |
A 3DOF aerodynamic model that makes use of data tabulated as a function of angle of
attack and Mach number.
|
AeroCoefficients |
A container for aerodynamic dimensionless coefficients such as lift coefficient (CL),
drag coefficient (CD), etc.
|
AeroCoefXAft |
A container for aerodynamic dimensionless coefficients such as lift coefficient
(CL), drag coefficient (CD), etc.
|
AeroMethods |
A set of utility methods for calculating various
aerodynamic analysis related properties.
|
AeroReference |
Class that serves as a container for aerodynamic reference quantities such as reference
area, span, chord length, and moment reference center.
|
Airspeeds |
A collection of static routines for calculating various airspeeds.
|
ConicalShock |
A class that computes the properties of a semi-infinite cone in
supersonic flow.
|
ControlAero3DOFTabular |
A 3DOF aerodynamic model of flight control deflection that makes use of
data tabulated as a function of angle of attack, Mach number, and
control deflection angle.
|
ControlHMLinearizedTabular |
A model of flight control surface aerodynamic hinge-moments that
makes use of a linearized component build-up where each component is data
tabulated as a function of Mach number.
|
Isentropic |
A set of utility methods for calculating isentropic flow properties in a gas.
|
IsentropicMeEvaluator |
Used by Isentropic.Me() and a root solver to iteratively determine the local Mach
number at the entrance or exit of a duct with a sonic condition at the throat.
|
ShockBetaEvaluator |
Used by ShockMethods.os_beta() and a root solver to iteratively determine beta.
|
ShockMachEvaluator |
Used by ShockMethods.os_mach() and a root solver to iteratively determine Mach number
for an oblique shock when given the incline and shock angles.
|
ShockMachNuEvaluator |
Used by ShockMethods.pm_Mach() and a root solver to iteratively determine Mach number
for a given Prandtl-Meyer function value.
|
ShockMethods |
A set of utility methods for calculating the properties
across shock waves.
|
StdAtmos |
An abstract class that provides standard functionality
for all atmosphere models that sub-class off of this
one.
|
StdAtmos1962 |
This class provides methods for calculating the atmospheric
properties of the U.S.
|
StdAtmos1976 |
This class provides methods for calculating the atmospheric
properties of the ICAO 1976 Standard Atmosphere to
an arbitrary altitude (above 3280839.9 ft the values are constant).
|