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. x/c y/c X(in) Y(in) Z(in) X(m) Y(m) Z(m) Cp 0.90000 -0.01223 11.685 20.000 -0.628 0.29680 0.50800 -0.01596 0.1720 0.80000 -0.02175 9.880 20.000 -0.737 0.25096 0.50800 -0.01872 0.0094 0.70000 -0.02994 8.076 20.000 -0.821 0.20514 0.50800 -0.02086 -0.0459 0.60000 -0.03673 6.273 20.000 -0.881 0.15934 0.50800 -0.02237 -0.0897 0.50000 -0.04183 4.471 20.000 -0.910 0.11356 0.50800 -0.02310 -0.1210 0.40000 -0.04474 2.670 20.000 -0.899 0.06782 0.50800 -0.02284 -0.1387 0.30000 -0.04456 0.871 20.000 -0.833 0.02213 0.50800 -0.02116 -0.1470 0.25000 -0.04290 -0.027 20.000 -0.772 -0.00068 0.50800 -0.01960 -0.1418 0.20000 -0.03979 -0.924 20.000 -0.684 -0.02348 0.50800 -0.01739 -0.1105 0.15000 -0.03507 -1.821 20.000 -0.568 -0.04625 0.50800 -0.01443 -0.0396 0.12500 -0.03231 -2.269 20.000 -0.503 -0.05763 0.50800 -0.01277 -0.0073 0.10000 -0.02938 -2.717 20.000 -0.434 -0.06901 0.50800 -0.01103 0.0208 0.07500 -0.02626 -3.165 20.000 -0.362 -0.08038 0.50800 -0.00921 0.0354 0.05000 -0.02261 -3.612 20.000 -0.281 -0.09175 0.50800 -0.00714 0.0386 0.04000 -0.02081 -3.791 20.000 -0.243 -0.09629 0.50800 -0.00616 0.0417 0.03000 -0.01861 -3.969 20.000 -0.197 -0.10082 0.50800 -0.00500 0.0552 0.02000 -0.01569 -4.147 20.000 -0.138 -0.10534 0.50800 -0.00350 0.1147 0.01000 -0.01121 -4.325 20.000 -0.051 -0.10985 0.50800 -0.00131 0.3044 0.00500 -0.00756 -4.413 20.000 0.017 -0.11208 0.50800 0.00044 0.5578 0.00000 0.00000 -4.497 20.000 0.157 -0.11423 0.50800 0.00399 0.9988 0.01000 0.02434 -4.302 20.000 0.589 -0.10928 0.50800 0.01496 0.2784 0.01500 0.02885 -4.210 20.000 0.667 -0.10693 0.50800 0.01694 -0.1324 0.02000 0.03272 -4.117 20.000 0.734 -0.10458 0.50800 0.01863 -0.3399 0.02500 0.03614 -4.025 20.000 0.792 -0.10224 0.50800 0.02011 -0.5036 0.03000 0.03921 -3.933 20.000 0.844 -0.09990 0.50800 0.02144 -0.6725 0.04000 0.04456 -3.750 20.000 0.934 -0.09525 0.50800 0.02373 -0.7664 0.05000 0.04915 -3.567 20.000 1.010 -0.09060 0.50800 0.02565 -0.8717 0.07500 0.05802 -3.112 20.000 1.154 -0.07904 0.50800 0.02932 -0.9478 0.10000 0.06435 -2.658 20.000 1.252 -0.06751 0.50800 0.03181 -1.0489 0.12500 0.06880 -2.205 20.000 1.316 -0.05602 0.50800 0.03344 -1.0604 0.15000 0.07182 -1.754 20.000 1.355 -0.04455 0.50800 0.03442 -1.0260 0.20000 0.07497 -0.852 20.000 1.380 -0.02165 0.50800 0.03506 -0.9582 0.25000 0.07595 0.048 20.000 1.366 0.00121 0.50800 0.03471 -0.7987 0.30000 0.07552 0.947 20.000 1.327 0.02405 0.50800 0.03369 -0.6829 0.35000 0.07388 1.845 20.000 1.266 0.04687 0.50800 0.03216 -0.6100 0.40000 0.07134 2.743 20.000 1.189 0.06968 0.50800 0.03020 -0.5526 0.45000 0.06802 3.641 20.000 1.098 0.09247 0.50800 0.02789 -0.4984 0.50000 0.06406 4.538 20.000 0.996 0.11525 0.50800 0.02529 -0.4411 0.55000 0.05955 5.434 20.000 0.883 0.13803 0.50800 0.02243 -0.3900 0.60000 0.05456 6.330 20.000 0.762 0.16079 0.50800 0.01935 -0.3535 0.65000 0.04914 7.227 20.000 0.633 0.18355 0.50800 0.01608 -0.3107 0.70000 0.04335 8.122 20.000 0.497 0.20631 0.50800 0.01263 -0.2555 0.75000 0.03720 9.018 20.000 0.355 0.22905 0.50800 0.00902 -0.2127 0.80000 0.03071 9.913 20.000 0.207 0.25180 0.50800 0.00526 -0.1814 0.85000 0.02389 10.808 20.000 0.053 0.27453 0.50800 0.00135 -0.1376 0.90000 0.01673 11.703 20.000 -0.107 0.29727 0.50800 -0.00273 -0.0897 0.95000 0.00919 12.598 20.000 -0.274 0.31999 0.50800 -0.00697 -0.0073