Non-dimensional airfoil pressure tap locations provided for reference.								
The pressure tap row is oriented perpendicular to the leading edge.								
Dimensional coordinates are for the model at AoA = 0 deg. as shown in the CAD file.								
								
x/c	y/c	X(in)	Y(in)	Z(in)	X(m)	Y(m)	Z(m)	Cp
0.9500	0.0081	22.062	0.423	-0.292	0.56037	0.01075	-0.00741 -0.0404
0.9000	0.0145	20.789	1.696	-0.523	0.52804	0.04308	-0.01328 -0.0553
0.8000	0.0262	18.243	4.242	-0.946	0.46338	0.10774	-0.02403 -0.0921
0.7000	0.0366	15.698	6.787	-1.320	0.39873	0.17240	-0.03354 -0.1161
0.6000	0.0456	13.152	9.333	-1.644	0.33407	0.23706	-0.04176 -0.1440
0.5000	0.0529	10.607	11.879	-1.907	0.26941	0.30172	-0.04844 -0.1645
0.4000	0.0580	8.061	14.424	-2.090	0.20475	0.36638	-0.05309 -0.1871
0.3000	0.0600	5.515	16.970	-2.162	0.14009	0.43103	-0.05491 -0.2122
0.2500	0.0594	4.243	18.243	-2.140	0.10776	0.46336	-0.05435 -0.2214
0.2000	0.0574	2.970	19.515	-2.066	0.07543	0.49569	-0.05249 -0.2278
0.1500	0.0535	1.697	20.788	-1.925	0.04310	0.52802	-0.04890 -0.2394
0.1200	0.0499	0.933	21.552	-1.796	0.02371	0.54742	-0.04563 -0.2361
0.0900	0.0451	0.170	22.316	-1.622	0.00431	0.56682	-0.04121 -0.2242
0.0700	0.0409	-0.339	22.825	-1.472	-0.00862 0.57975 -0.03738 -0.2221
0.0500	0.0355	-0.849	23.334	-1.280	-0.02155 0.59268 -0.03251 -0.1957
0.0300	0.0284	-1.358	23.843	-1.023	-0.03449 0.60561 -0.02598 -0.1588
0.0200	0.0236	-1.612	24.098	-0.850	-0.04095 0.61208 -0.02158 -0.1019
0.0030	0.0095	-2.045	24.530	-0.343	-0.05194 0.62307 -0.00871 0.2441
0.0000	0.0000	-2.121	24.607	0.000	-0.05388 0.62501 0.00000 0.4622
0.0030	-0.0095	-2.045	24.530	0.343	-0.05194 0.62307 0.00871 0.2195
0.0100	-0.0170	-1.867	24.352	0.613	-0.04742 0.61854 0.01558 -0.0059
0.0200	-0.0236	-1.612	24.098	0.850	-0.04095 0.61208 0.02158 -0.1224
0.0300	-0.0284	-1.358	23.843	1.023	-0.03449 0.60561 0.02598 -0.1744
0.0400	-0.0323	-1.103	23.588	1.162	-0.02802 0.59915 0.02953 -0.2004
0.0550	-0.0370	-0.721	23.207	1.333	-0.01832 0.58945 0.03385 -0.2179
0.0750	-0.0420	-0.212	22.697	1.513	-0.00539 0.57652 0.03842 -0.2297
0.1200	-0.0499	0.933	21.552	1.796	0.02371	0.54742	0.04563	-0.2348
0.1400	-0.0524	1.442	21.043	1.886	0.03664	0.53449	0.04791	-0.2354
0.1600	-0.0544	1.952	20.534	1.960	0.04957	0.52156	0.04978	-0.2274
0.1800	-0.0561	2.461	20.025	2.019	0.06250	0.50862	0.05129	-0.2292
0.2000	-0.0574	2.970	19.515	2.066	0.07543	0.49569	0.05249	-0.2188
0.2400	-0.0591	3.988	18.497	2.130	0.10130	0.46983	0.05409	-0.2225
0.2800	-0.0599	5.006	17.479	2.158	0.12716	0.44397	0.05482	-0.2141
0.3200	-0.0599	6.025	16.461	2.158	0.15302	0.41810	0.05483	-0.2058
0.3600	-0.0593	7.043	15.442	2.135	0.17889	0.39224	0.05422	-0.1939
0.4000	-0.0580	8.061	14.424	2.090	0.20475	0.36638	0.05309	-0.1845
0.4500	-0.0558	9.334	13.151	2.010	0.23708	0.33405	0.05106	-0.1724
0.5000	-0.0529	10.607	11.879	1.907	0.26941	0.30172	0.04844	-0.1620
0.5500	-0.0495	11.879	10.606	1.784	0.30174	0.26939	0.04532	-0.1457
0.6000	-0.0456	13.152	9.333	1.644	0.33407	0.23706	0.04176	-0.1340
0.6500	-0.0413	14.425	8.060	1.489	0.36640	0.20473	0.03782	-0.1209
0.7000	-0.0366	15.698	6.787	1.320	0.39873	0.17240	0.03354	-0.1079
0.8000	-0.0262	18.243	4.242	0.946	0.46338	0.10774	0.02403	-0.0893
0.9000	-0.0145	20.789	1.696	0.523	0.52804	0.04308	0.01328	-0.0642