def f_q_vlm(x, velocity, airplane):
ap = vlm3(
airplane=airplane,
op_point=OperatingPoint(
velocity=velocity,
alpha=0,
beta=0,
p=0,
q=x,
r=0,
),
)
ap.run()
return {"CL": check_if_nan(ap.CL), "CD": check_if_nan(ap.CDi), "CY": check_if_nan(ap.CY),
"Cm": check_if_nan(ap.Cm),
"Cn": check_if_nan(ap.Cn),"Cl":check_if_nan(ap.Cl)}
def f_p(x, velocity):
airplane = create_aircraft()
try:
airplane.set_spanwise_paneling_everywhere(
8) # Set the resolution of your analysis
opti = cas.Opti()
ap = Casll1( # Set up the AeroProblem
airplane=airplane,
op_point=OperatingPoint(
density=1.225, # kg/m^3
viscosity=1.81e-5, # kg/m-s
velocity=velocity, # m/s070
mach=0, # Freestream mach number
alpha=0, # In degrees
beta=0, # In degrees
p=x, # About the body x-axis, in rad/sec
q=0, # About the body y-axis, in rad/sec
r=0, # About the body z-axis, in rad/sec
),
opti=opti # Pass it an optimization environment to work in
)
p_opts = {}
s_opts = {}
s_opts["mu_strategy"] = "adaptive"
opti.solver('ipopt', p_opts, s_opts)
try:
sol = opti.solve()
except RuntimeError:
sol = opti.debug
ap_sol = copy.deepcopy(ap)
ap_sol.substitute_solution(sol)
values = {
"CL": check_if_nan(ap_sol.CL),
"CD": check_if_nan(ap_sol.CD),
"CY": check_if_nan(ap_sol.CY),
"Cl": check_if_nan(ap_sol.Cl),
"Cm": check_if_nan(ap_sol.Cm),
"Cn": check_if_nan(ap_sol.Cn)
}
except:
values = f_p_vlm(x, velocity, airplane)
return values