def Rate_of_twist(T):
constant = T / (4 * Wing.Area_cell()**2 * WingStress.shear_modulus)
integral = Wing.HSpar1 / Wing.ThSpar1
integral += 2 * Wing.length_Skin_x_c(Wing.ChSpar1,
Wing.ChSpar2) / Wing.ThSkin
integral += Wing.HSpar2 / Wing.ThSpar2
dthetadz = constant / integral
return dthetadz
def Moment_shearflow(n):
qmoment = WingStress.M / (2 * Wing.Area_cell())
q_moment = np.array([])
for _ in range(n + 1):
q_moment = np.append(q_moment, qmoment)
return q_moment * ureg("N/m")