def run_test1():
fc = FlightConditions(65.0,1500.)
print fc.atm.density
print fc.atm.viscosity
print fc.atm.soundSpeed
print fc.Re
alt = get_density_altitude(1.0)
fc.set_altitude(alt)
print fc.atm.density
print const.get_gravity_acceleration(10000)
def __init__(self,altitude,dT=0,gas='air'):
altitude = float(altitude)
P0 = 101325.0
T0 = 288.15
G0 = 9.80665
R = 287.04
GAMMA = 1.4
if altitude<11000:
T = T0 - 6.5 * altitude / 1000 + dT
P = P0 * (1 - 0.0065 * altitude / T0) ** 5.2561
else:
T11 = T0 - 6.5 * 11000 / 1000 + dT
P11 = P0 * (1 - 0.0065 * 11000 / T0) ** 5.2561
T = T11 + dT
P = P11 * exp(-G0 / (R * T11) * (altitude - 11000))
rho = P / (R * T)
a = (GAMMA * R * T) ** 0.5
self.dT = dT
self.gas = gas
self.altitude = altitude
self.temperature = T
self.pressure = P
self.soundSpeed = a
self.density = rho
self.set_sutherland_viscosity(self.gas)
self.g = const.get_gravity_acceleration(altitude)