Non-dimensional airfoil pressure tap locations provided for reference.																							
Dimensional coordinates are for the model at AoA = 2 deg. as shown in the CAD file.	
Data were digitized from plots in NASA/TP--2016-218348.
																																									
x/c	y/c	X(in)	Y(in)	Z(in)	X(m)	Y(m)	Z(m)	Cp															
1.00000	0.00000	53.967	20.000	-1.885	1.37076	0.50800	-0.04787 0.1339
0.97500	0.00530	52.182	20.000	-1.442	1.32542	0.50800	-0.03662 0.0710
0.95000	0.00920	50.392	20.000	-1.097	1.27997	0.50800	-0.02786 0.0164
0.92500	0.01300	48.603	20.000	-0.760	1.23452	0.50800	-0.01930 -0.0301
0.90000	0.01670	46.814	20.000	-0.429	1.18907	0.50800	-0.01090 -0.0683
0.85000	0.02390	43.234	20.000	0.212	1.09814	0.50800	0.00539	-0.1284
0.80000	0.03070	39.653	20.000	0.828	1.00719	0.50800	0.02104	-0.1831
0.75000	0.03720	36.072	20.000	1.421	0.91622	0.50800	0.03609	-0.2268
0.70000	0.04330	32.489	20.000	1.989	0.82523	0.50800	0.05052	-0.2678
0.65000	0.04920	28.906	20.000	2.532	0.73421	0.50800	0.06430	-0.3115
0.60000	0.05460	25.322	20.000	3.047	0.64317	0.50800	0.07739	-0.3552
0.55000	0.05960	21.737	20.000	3.532	0.55211	0.50800	0.08971	-0.3989
0.50000	0.06410	18.150	20.000	3.982	0.46101	0.50800	0.10114	-0.4399
0.45000	0.06800	14.562	20.000	4.393	0.36988	0.50800	0.11157	-0.4891
0.40000	0.07130	10.973	20.000	4.757	0.27871	0.50800	0.12082	-0.5383
0.36000	0.07340	8.100	20.000	5.008	0.20573	0.50800	0.12721	-0.5847
0.32000	0.07500	5.225	20.000	5.219	0.13272	0.50800	0.13255	-0.6257
0.28000	0.07580	2.349	20.000	5.381	0.05967	0.50800	0.13667	-0.6831
0.24000	0.07590	-0.529	20.000	5.486	-0.01343 0.50800 0.13934 -0.7322
0.21000	0.07530	-2.689	20.000	5.520	-0.06830 0.50800 0.14020 -0.7814
0.18000	0.07410	-4.851	20.000	5.506	-0.12321 0.50800 0.13986 -0.8361
0.15000	0.07180	-7.015	20.000	5.420	-0.17818 0.50800 0.13768 -0.9372
0.12000	0.06810	-9.183	20.000	5.224	-0.23326 0.50800 0.13268 -0.9973
0.09000	0.06210	-11.357	20.000	4.871	-0.28847 0.50800 0.12372 -0.9973
0.06530	0.05490	-13.158	20.000	4.417	-0.33421 0.50800 0.11220 -0.9290
0.04000	0.04460	-14.999	20.000	3.737	-0.38098 0.50800 0.09491 -0.7350
0.02000	0.03280	-16.468	20.000	2.935	-0.41827 0.50800 0.07456 -0.4262
0.01000	0.02440	-17.208	20.000	2.356	-0.43709 0.50800 0.05985 -0.0464
0.00410	0.01730	-17.655	20.000	1.865	-0.44844 0.50800 0.04737 0.4235
0.00010	0.00910	-17.965	20.000	1.283	-0.45631 0.50800 0.03258 0.8841
0.00000	0.00000	-17.989	20.000	0.628	-0.45692 0.50800 0.01596 0.9536
0.00400	-0.00660 -17.718 20.000	0.140	-0.45004 0.50800 0.00357 0.3279
0.01000	-0.01130 -17.298 20.000	-0.206	-0.43936 0.50800 -0.00524 0.0601
0.02000	-0.01570 -16.590 20.000	-0.552	-0.42137 0.50800 -0.01402 -0.1038
0.03500	-0.01980 -15.520 20.000	-0.883	-0.39422 0.50800 -0.02244 -0.1202
0.05500	-0.02340 -14.090 20.000	-1.195	-0.35789 0.50800 -0.03036 -0.0984
0.07500	-0.02630 -12.658 20.000	-1.450	-0.32152 0.50800 -0.03682 -0.0820
0.10000	-0.02940 -10.867 20.000	-1.737	-0.27603 0.50800 -0.04413 -0.0820
0.15000	-0.03510 -7.284	20.000	-2.272	-0.18501 0.50800 -0.05770 -0.1339
0.20000	-0.03980 -3.698	20.000	-2.738	-0.09392 0.50800 -0.06954 -0.1995
0.25000	-0.04290 -0.108	20.000	-3.087	-0.00274 0.50800 -0.07840 -0.2350
0.30000	-0.04460 3.486	20.000	-3.333	0.08854	0.50800	-0.08466 -0.2404
0.35000	-0.04510 7.082	20.000	-3.498	0.17989	0.50800	-0.08884 -0.2295
0.40000	-0.04480 10.681	20.000	-3.596	0.27130	0.50800	-0.09135 -0.2213
0.45000	-0.04360 14.282	20.000	-3.640	0.36275	0.50800	-0.09247 -0.2104
0.55000	-0.03950 21.488	20.000	-3.597	0.54578	0.50800	-0.09137 -0.1831
0.65000	-0.03350 28.698	20.000	-3.418	0.72893	0.50800	-0.08681 -0.1448
0.75000	-0.02600 35.913	20.000	-3.129	0.91218	0.50800	-0.07947 -0.1093
0.85000	-0.01720 43.131	20.000	-2.743	1.09552	0.50800	-0.06966 -0.0574
0.95000	-0.00690 50.352	20.000	-2.258	1.27894	0.50800	-0.05735 0.0355