##### Tangential force calculation
CT = (pt1_star + pt2_star * cosa + pt3_star * cosa**3) * sina**2
##### Conversion to wind axes
CL = CN * cosa + CT * sina
CD = CN * sina - CT * cosa
CM = np.zeros_like(CL) # TODO
return CL, CD, CM
if __name__ == '__main__':
af = Airfoil("naca0012")
alpha = np.linspace(0, 360, 721)
CL, CD, CM = airfoil_coefficients_post_stall(af, alpha)
from aerosandbox.tools.pretty_plots import plt, show_plot, set_ticks
fig, ax = plt.subplots(1, 2, figsize=(8, 5))
plt.sca(ax[0])
plt.plot(alpha, CL)
plt.xlabel("AoA")
plt.ylabel("CL")
set_ticks(45, 15, 0.5, 0.1)
plt.sca(ax[1])
plt.plot(alpha, CD)
plt.xlabel("AoA")
plt.ylabel("CD")
set_ticks(45, 15, 0.5, 0.1)
show_plot()
"Reynolds Number [-]",
)
##### Plot Polars
fig, ax = plt.subplots(2, 2, figsize=(8, 8))
Re = 1e6
alpha_lowres = np.linspace(-15, 15, 31)
ma = alpha
mCL = af.CL_function(alpha, Re)
mCD = af.CD_function(alpha, Re)
xf_run = asb.XFoil(af, Re=Re, max_iter=20).alpha(alpha_lowres)
xa = xf_run["alpha"]
xCL = xf_run["CL"]
xCD = xf_run["CD"]
plt.sca(ax[0, 0])
plt.plot(ma, mCL)
plt.plot(xa, xCL, ".")
plt.xlabel("Angle of Attack [deg]")
plt.ylabel("Lift Coefficient $C_L$ [-]")
plt.sca(ax[0, 1])
plt.plot(ma, mCD)
plt.plot(xa, xCD, ".")
plt.ylim(0, 0.05)
plt.xlabel("Angle of Attack [deg]")
plt.ylabel("Drag Coefficient $C_D$ [-]")
plt.sca(ax[1, 0])
plt.plot(mCD, mCL)
plt.plot(xCD, xCL, ".")
from aerosandbox.tools.pretty_plots import plt, show_plot, equal
vars_to_plot = {
**dyn.state,
"alpha" : dyn.alpha,
"beta" : dyn.beta,
"speed" : dyn.speed,
"altitude": dyn.altitude,
"CL" : aero["CL"],
"CY" : aero["CY"],
"CD" : aero["CD"],
"Cl" : aero["Cl"],
"Cm" : aero["Cm"],
"Cn" : aero["Cn"],
}
fig, axes = plt.subplots(6, 4, figsize=(15, 10), sharex=True)
for var_to_plot, ax in zip(vars_to_plot.items(), axes.flatten(order="F")):
plt.sca(ax)
k, v = var_to_plot
plt.plot(dyn.time, v)
plt.ylabel(k)
show_plot()
fig, ax = plt.subplots()
plt.plot(dyn.xe, dyn.altitude, "k")
sc = plt.scatter(dyn.xe, dyn.altitude, c=dyn.speed, cmap=plt.get_cmap("rainbow"), zorder=4)
plt.axis('equal')
plt.colorbar(label="Airspeed [m/s]")
show_plot("Trajectory using `asb.AeroBuildup` Flight Dynamics", "$x_e$", "$-z_e$")