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	24.824	6.596	-0.292	0.63053	0.16754	-0.00741 0.0236
0.9000	0.0145	23.265	7.496	-0.523	0.59094	0.19040	-0.01328 -0.0179
0.8000	0.0262	20.147	9.296	-0.946	0.51175	0.23612	-0.02403 -0.0613
0.7000	0.0366	17.030	11.096	-1.320	0.43255	0.28184	-0.03354 -0.1211
0.6000	0.0456	13.912	12.896	-1.644	0.35337	0.32756	-0.04176 -0.1657
0.5000	0.0529	10.794	14.696	-1.907	0.27418	0.37328	-0.04844 -0.1996
0.4000	0.0580	7.677	16.496	-2.090	0.19498	0.41900	-0.05309 -0.2220
0.3000	0.0600	4.559	18.296	-2.162	0.11579	0.46472	-0.05491 -0.2905
0.2500	0.0594	3.000	19.196	-2.140	0.07620	0.48758	-0.05435 -0.3089
0.2000	0.0574	1.441	20.096	-2.066	0.03660	0.51044	-0.05249 -0.3395
0.1500	0.0535	-0.118	20.996	-1.925	-0.00299 0.53330 -0.04890 -0.3472
0.1200	0.0499	-1.053	21.536	-1.796	-0.02675 0.54702 -0.04563 -0.3432
0.0900	0.0451	-1.988	22.076	-1.622	-0.05051 0.56074 -0.04121 -0.3373
0.0700	0.0409	-2.612	22.436	-1.472	-0.06634 0.56988 -0.03738 -0.3311
0.0500	0.0355	-3.235	22.796	-1.280	-0.08218 0.57902 -0.03251 -0.2851
0.0300	0.0284	-3.859	23.156	-1.023	-0.09802 0.58817 -0.02598 -0.2365
0.0200	0.0236	-4.171	23.336	-0.850	-0.10594 0.59274 -0.02158 -0.1558
0.0030	0.0095	-4.701	23.642	-0.343	-0.11940 0.60051 -0.00871 0.3674
0.0000	0.0000	-4.794	23.696	0.000	-0.12177 0.60188 0.00000 0.7098
0.0030	-0.0095	-4.701	23.642	0.343	-0.11940 0.60051 0.00871 0.4021
0.0100	-0.0170	-4.483	23.516	0.613	-0.11386 0.59731 0.01558 0.0328
0.0200	-0.0236	-4.171	23.336	0.850	-0.10594 0.59274 0.02158 -0.1594
0.0300	-0.0284	-3.859	23.156	1.023	-0.09802 0.58817 0.02598 -0.2363
0.0400	-0.0323	-3.547	22.976	1.162	-0.09010 0.58360 0.02953 -0.2866
0.0550	-0.0370	-3.080	22.706	1.333	-0.07822 0.57674 0.03385 -0.3296
0.0750	-0.0420	-2.456	22.346	1.513	-0.06238 0.56759 0.03842 -0.3310
0.1200	-0.0499	-1.053	21.536	1.796	-0.02675 0.54702 0.04563 -0.3440
0.1400	-0.0524	-0.430	21.176	1.886	-0.01091 0.53788 0.04791 -0.3339
0.1600	-0.0544	0.194	20.816	1.960	0.00493	0.52873	0.04978	-0.3289
0.1800	-0.0561	0.818	20.456	2.019	0.02077	0.51959	0.05129	-0.3213
0.2000	-0.0574	1.441	20.096	2.066	0.03660	0.51044	0.05249	-0.3136
0.2400	-0.0591	2.688	19.376	2.130	0.06828	0.49215	0.05409	-0.3102
0.2800	-0.0599	3.935	18.656	2.158	0.09996	0.47387	0.05482	-0.2942
0.3200	-0.0599	5.182	17.936	2.158	0.13163	0.45558	0.05483	-0.2898
0.3600	-0.0593	6.429	17.216	2.135	0.16331	0.43729	0.05422	-0.2570
0.4000	-0.0580	7.677	16.496	2.090	0.19498	0.41900	0.05309	-0.2487
0.4500	-0.0558	9.235	15.596	2.010	0.23458	0.39614	0.05106	-0.2285
0.5000	-0.0529	10.794	14.696	1.907	0.27418	0.37328	0.04844	-0.2147
0.5500	-0.0495	12.353	13.796	1.784	0.31377	0.35042	0.04532	-0.1876
0.6000	-0.0456	13.912	12.896	1.644	0.35337	0.32756	0.04176	-0.1710
0.6500	-0.0413	15.471	11.996	1.489	0.39296	0.30470	0.03782	-0.1363
0.7000	-0.0366	17.030	11.096	1.320	0.43255	0.28184	0.03354	-0.1142
0.8000	-0.0262	20.147	9.296	0.946	0.51175	0.23612	0.02403	-0.0923
0.9000	-0.0145	23.265	7.496	0.523	0.59094	0.19040	0.01328	-0.0238
0.9500	-0.0081	24.824	6.596	0.292	0.63053	0.16754	0.00741	0.0351