#NACA 23012 exp. results alpha = 0°10' M=0.62
# Cp=(Pfoil - Pinfinity)/q; q = rho*U^2/2
#columns
#    x    Cp
#Upper
0.648850002166  0.594351799714
1.00056308745  0.206219950622
3.45475808897  -0.457764109672
6.14544982025  -0.727560965045
8.6724130463  -0.885641269979
10.7411097154  -0.932091653311
13.3867544506  -0.89601940486
20.5760817776  -0.711551955646
24.6874864642  -0.627989777797
32.0344782778  -0.51406419197
36.8874258241  -0.465578030926
41.7412396587  -0.422973968034
46.8887252566  -0.374401178152
52.1834798805  -0.325785073851
56.3018148742  -0.289279681206
64.0975440724  -0.222280937324
74.2443799541  -0.119296573829
79.2445965262  -0.070767098367
89.5352362802  0.0557889721488
100.114350067  0.223606358557


#Lower
0.17672283103  -0.199904708277
0.791787586087  -0.376194395114
1.97600381167  -0.417022566812
3.58383505869  -0.334196734093
4.60692164422  -0.280954649803
7.54277298913  -0.21538528176
10.6345562438  -0.208593580803
15.7993676095  -0.277662753931
20.6661757699  -0.323290163295
26.2649976177  -0.339290509811
33.4785810196  -0.31952180881
38.4805301685  -0.282756529649
43.6288820548  -0.240065837917
48.7798328063  -0.215021440638
53.933382423  -0.207623337809
58.937930437  -0.188504353099
64.0880149002  -0.157577857669
69.2372330749  -0.120769264088
74.2383159354  -0.0781218867761
79.3866678217  -0.0354311950448
89.5343699918  0.0616710702993
100.114350067  0.223606358557