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)