def update_aero_trim(
self, velocity, altitude, CmTrim=0.0, loadFactor=1.0, mass=None, cg=None, inertia=None, CD0=None
):
"""
Updates results of aerodynamic analysis at trim condition using AVL solver. Stores the result
of analysis in self.aeroResults.
Parameters
----------
velocity : float, m/sec
true airspeed of the aircraft. If velocity<5 then it is treated as Mach number, otherwise
airspeed in m/sec.
altitude : float, m
density altitude at which analysis is performed
CmTrim : float
Required moment coefficient. By default CmTrim=0 - no pitching moment.
loadFactor : float
load factor can be used for gust analysis: analysis is performed with mass= mass*loadFactor
mass : float, kg
aircraft mass. If value is not defined then total aircraft mass will be calculated.
cg : array, m
center of gravity in format array([x,y,z]). If value is not specified then value will be
calculated
inertia : array, kg*m2
aircraft moment of inertia in format array([Ixx, Iyy, Izz]). Required for dynamic
stability calculation.
CD0 : float
parasite drag coefficient. If value is not specified then value will be calculated.
"""
aero = Aerodynamics(self)
fc = FlightConditionsAVL(self, velocity, altitude, CmTrim, loadFactor, mass, cg, inertia, CD0)
self.aeroResults = aero.run_trim(fc)
def get_aero_single_point(self,velocity=None,altitude=None,alpha=0.0,beta=0.0,
elevator=0.0,mass=None,cg=None,inertia=None,CD0=None):
"""
Performs aerodynamic analysis using AVL at given aircraft configuration and flight condtions.
Parameters
----------
velocity : float, m/sec
true airspeed of the aircraft. If velocity<5 then it is treated as Mach number, otherwise
airspeed in m/sec.
altitude : float, m
density altitude at which analysis is performed
alpha : float, deg
aircraft angle of attack
beta : float, deg
aircraft sideslip angle
elevator : float, deg
elevator deflection. positive direction is down.
mass : float, kg
aircraft mass. If value is not defined then total aircraft mass will be calculated.
cg : array, m
center of gravity in format array([x,y,z]). If value is not specified then value will be
calculated
inertia : array, kg*m2
aircraft moment of inertia in format array([Ixx, Iyy, Izz]). Required for dynamic
stability calculation.
CD0 : float
parasite drag coefficient. If value is not specified then value will be calculated.
"""
if velocity==None:
velocity = self.designGoals.cruiseSpeed
if altitude==None:
altitude = self.designGoals.cruiseAltitude
aero = Aerodynamics(self)
fc = FlightConditionsAVL(self,velocity,altitude,0,1,mass,cg,inertia,CD0)
alpha = float(alpha)
beta = float(beta)
elevator = float(elevator)
self.aeroResults = aero.run_single_point(fc,alpha,beta,elevator)
return self.aeroResults
