def aero_dat(Re, Ma, Kn, p_inf, q_inf, rho_inf, gamma_var, Cd_prev, Cl_prev):
	"""
	Constant aerdynamic coefficients - space shuttle example
	"""
	C_d = 0.84
	C_l = 0.84
	C_s = 0.0
	
	return [C_d, C_l, C_s]