NACA 0012 Airfoil M=0.0% P=0.0% T=12.0%
1	1.00126
0.996057	1.001812
0.984292	1.003443
0.964888	1.006082
0.938153	1.009619
0.904508	1.013914
0.864484	1.018809
0.818712	1.024135
0.767913	1.029717
0.71289	1.035374
0.654508	1.040917
0.593691	1.046149
0.531395	1.050854
0.468605	1.05481
0.406309	1.057789
0.345492	1.059575
0.28711	1.05998
0.232087	1.058866
0.181288	1.05616
0.135516	1.051863
0.095492	1.046049
0.061847	1.038859
0.035112	1.030473
0.015708	1.021088
0.003943	1.010884
0	1
0.003943	0.989116
0.015708	0.978912
0.035112	0.969527
0.061847	0.961141
0.095492	0.953951
0.135516	0.948137
0.181288	0.94384
0.232087	0.941134
0.28711	0.94002
0.345492	0.940425
0.406309	0.942211
0.468605	0.94519
0.531395	0.949146
0.593691	0.953851
0.654508	0.959083
0.71289	0.964626
0.767913	0.970283
0.818712	0.975865
0.864484	0.981191
0.904508	0.986086
0.938153	0.990381
0.964888	0.993918
0.984292	0.996557
0.996057	0.998188
1	0.99874
