# the main file
w = 60500  # N, standard aicraft mass
mdotfs = 0.048  # kg/second standard engine fuel flow per engine
rho0 = 1.225 # kg/m3 standard air density

lamda = -0.0065         # temperature gradient in ISA [K/m]
Temp0 = 288.15          # temperature at sea level in ISA [K]
R = 287.05          # specific gas constant [m^2/sec^2K]
g = 9.81            # [m/sec^2] (gravity constant)

