XFOIL Version 6.96 Calculated polar for: NPL 9626 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.9688 0.12417 0.12192 0.0075 1.0000 0.0104 -17.000 -0.9903 0.11475 0.11239 0.0023 1.0000 0.0103 -16.750 -1.0384 0.10054 0.09798 -0.0057 1.0000 0.0102 -16.500 -1.0761 0.08915 0.08642 -0.0123 1.0000 0.0102 -16.250 -1.1040 0.07995 0.07706 -0.0178 1.0000 0.0101 -16.000 -1.1293 0.07162 0.06857 -0.0228 1.0000 0.0101 -15.750 -1.1488 0.06438 0.06117 -0.0272 1.0000 0.0101 -15.500 -1.1650 0.05799 0.05462 -0.0310 1.0000 0.0101 -15.250 -1.1769 0.05253 0.04901 -0.0342 1.0000 0.0101 -15.000 -1.1849 0.04796 0.04429 -0.0366 1.0000 0.0101 -14.750 -1.1913 0.04393 0.04011 -0.0383 1.0000 0.0101 -14.500 -1.1941 0.04068 0.03671 -0.0393 1.0000 0.0102 -14.250 -1.1950 0.03788 0.03378 -0.0397 1.0000 0.0102 -14.000 -1.1943 0.03550 0.03128 -0.0394 1.0000 0.0102 -13.750 -1.1920 0.03347 0.02912 -0.0387 1.0000 0.0103 -13.500 -1.1887 0.03168 0.02721 -0.0376 1.0000 0.0103 -13.250 -1.1915 0.02942 0.02479 -0.0355 1.0000 0.0104 -13.000 -1.1916 0.02755 0.02277 -0.0331 1.0000 0.0104 -12.750 -1.1891 0.02599 0.02110 -0.0304 1.0000 0.0105 -12.500 -1.1835 0.02470 0.01970 -0.0277 1.0000 0.0106 -12.250 -1.1725 0.02353 0.01844 -0.0258 1.0000 0.0107 -12.000 -1.1589 0.02249 0.01732 -0.0242 1.0000 0.0108 -11.750 -1.1435 0.02155 0.01631 -0.0227 1.0000 0.0109 -11.500 -1.1268 0.02069 0.01538 -0.0213 1.0000 0.0110 -11.250 -1.1091 0.01989 0.01452 -0.0200 1.0000 0.0111 -11.000 -1.0907 0.01914 0.01370 -0.0188 1.0000 0.0113 -10.750 -1.0717 0.01843 0.01294 -0.0176 1.0000 0.0114 -10.500 -1.0523 0.01777 0.01221 -0.0163 1.0000 0.0115 -10.250 -1.0328 0.01713 0.01152 -0.0151 1.0000 0.0117 -10.000 -1.0132 0.01653 0.01086 -0.0138 1.0000 0.0119 -9.750 -0.9936 0.01597 0.01025 -0.0124 1.0000 0.0120 -9.500 -0.9742 0.01544 0.00967 -0.0110 1.0000 0.0122 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0.0350 -4.500 -0.4131 0.00893 0.00299 -0.0145 0.9532 0.0387 -4.250 -0.3863 0.00871 0.00280 -0.0142 0.9429 0.0463 -4.000 -0.3600 0.00849 0.00263 -0.0137 0.9312 0.0572 -3.750 -0.3336 0.00830 0.00246 -0.0133 0.9186 0.0684 -3.500 -0.3077 0.00806 0.00228 -0.0128 0.9045 0.0876 -3.250 -0.2827 0.00771 0.00207 -0.0122 0.8889 0.1314 -3.000 -0.2584 0.00725 0.00185 -0.0116 0.8717 0.2018 -2.750 -0.2331 0.00695 0.00169 -0.0110 0.8527 0.2546 -2.500 -0.2073 0.00673 0.00158 -0.0106 0.8324 0.2984 -2.250 -0.1811 0.00654 0.00148 -0.0102 0.8118 0.3416 -2.000 -0.1549 0.00638 0.00140 -0.0098 0.7908 0.3837 -1.750 -0.1285 0.00624 0.00132 -0.0095 0.7693 0.4223 -1.500 -0.1030 0.00601 0.00125 -0.0090 0.7462 0.4848 -1.250 -0.0773 0.00584 0.00120 -0.0086 0.7219 0.5427 -1.000 -0.0506 0.00578 0.00117 -0.0083 0.6968 0.5795 -0.750 -0.0243 0.00571 0.00114 -0.0079 0.6709 0.6197 -0.500 0.0020 0.00565 0.00113 -0.0075 0.6465 0.6605 -0.250 0.0283 0.00558 0.00114 -0.0071 0.6234 0.7036 0.000 0.0541 0.00554 0.00116 -0.0065 0.5998 0.7472 0.250 0.0805 0.00553 0.00118 -0.0061 0.5740 0.7805 0.500 0.1072 0.00559 0.00121 -0.0057 0.5483 0.8057 0.750 0.1341 0.00563 0.00125 -0.0054 0.5274 0.8272 1.000 0.1611 0.00567 0.00130 -0.0050 0.5092 0.8484 1.250 0.1881 0.00573 0.00135 -0.0047 0.4925 0.8678 1.500 0.2151 0.00581 0.00142 -0.0043 0.4744 0.8849 1.750 0.2420 0.00590 0.00148 -0.0040 0.4567 0.8998 2.000 0.2690 0.00600 0.00155 -0.0036 0.4415 0.9135 2.250 0.2959 0.00611 0.00162 -0.0033 0.4257 0.9262 2.500 0.3227 0.00623 0.00170 -0.0029 0.4097 0.9379 3.000 0.3773 0.00647 0.00188 -0.0024 0.3815 0.9575 3.250 0.4066 0.00663 0.00198 -0.0026 0.3639 0.9650 3.500 0.4358 0.00680 0.00208 -0.0028 0.3431 0.9722 3.750 0.4678 0.00704 0.00220 -0.0037 0.3079 0.9766 4.000 0.4962 0.00755 0.00241 -0.0041 0.2429 0.9826 4.250 0.5274 0.00853 0.00285 -0.0055 0.1301 0.9851 4.500 0.5612 0.00920 0.00322 -0.0071 0.0717 0.9871 4.750 0.5957 0.00955 0.00347 -0.0087 0.0578 0.9895 5.000 0.6299 0.00980 0.00370 -0.0102 0.0538 0.9922 5.250 0.6643 0.01012 0.00398 -0.0118 0.0494 0.9944 5.500 0.7008 0.01033 0.00420 -0.0137 0.0475 0.9960 5.750 0.7362 0.01058 0.00444 -0.0155 0.0454 0.9977 6.000 0.7701 0.01091 0.00476 -0.0170 0.0428 0.9993 6.250 0.7983 0.01119 0.00505 -0.0173 0.0412 1.0000 6.500 0.8199 0.01136 0.00524 -0.0161 0.0400 1.0000 6.750 0.8413 0.01157 0.00545 -0.0149 0.0385 1.0000 7.000 0.8621 0.01184 0.00571 -0.0136 0.0369 1.0000 7.250 0.8819 0.01221 0.00610 -0.0122 0.0352 1.0000 7.500 0.9040 0.01239 0.00630 -0.0111 0.0342 1.0000 7.750 0.9259 0.01262 0.00653 -0.0100 0.0329 1.0000 8.000 0.9477 0.01287 0.00678 -0.0089 0.0316 1.0000 8.250 0.9676 0.01332 0.00722 -0.0075 0.0301 1.0000 8.500 0.9903 0.01354 0.00747 -0.0066 0.0293 1.0000 8.750 1.0127 0.01380 0.00775 -0.0056 0.0283 1.0000 9.000 1.0353 0.01408 0.00803 -0.0047 0.0273 1.0000 9.250 1.0575 0.01442 0.00837 -0.0039 0.0263 1.0000 9.500 1.0786 0.01489 0.00885 -0.0028 0.0253 1.0000 9.750 1.1016 0.01520 0.00920 -0.0021 0.0246 1.0000 10.000 1.1245 0.01553 0.00956 -0.0014 0.0237 1.0000 10.250 1.1469 0.01590 0.00993 -0.0007 0.0228 1.0000 10.500 1.1668 0.01649 0.01053 0.0004 0.0217 1.0000 10.750 1.1885 0.01692 0.01101 0.0012 0.0211 1.0000 11.000 1.2097 0.01737 0.01150 0.0021 0.0203 1.0000 11.250 1.2303 0.01786 0.01201 0.0030 0.0195 1.0000 11.500 1.2486 0.01851 0.01268 0.0042 0.0187 1.0000 11.750 1.2633 0.01940 0.01363 0.0059 0.0180 1.0000 12.000 1.2815 0.01998 0.01427 0.0071 0.0177 1.0000 12.250 1.2979 0.02064 0.01500 0.0085 0.0173 1.0000 12.500 1.3113 0.02133 0.01576 0.0104 0.0169 1.0000 12.750 1.3233 0.02209 0.01657 0.0124 0.0166 1.0000 13.000 1.3345 0.02294 0.01747 0.0143 0.0163 1.0000 13.250 1.3445 0.02390 0.01850 0.0161 0.0160 1.0000 13.500 1.3527 0.02505 0.01972 0.0178 0.0158 1.0000 13.750 1.3584 0.02648 0.02121 0.0195 0.0156 1.0000 14.000 1.3606 0.02828 0.02310 0.0210 0.0153 1.0000 14.250 1.3578 0.03069 0.02563 0.0224 0.0151 1.0000 14.500 1.3613 0.03273 0.02777 0.0230 0.0150 1.0000 14.750 1.3662 0.03477 0.02991 0.0232 0.0150 1.0000 15.000 1.3697 0.03708 0.03232 0.0232 0.0149 1.0000 15.250 1.3718 0.03964 0.03499 0.0229 0.0148 1.0000 15.500 1.3724 0.04250 0.03796 0.0224 0.0148 1.0000 15.750 1.3716 0.04564 0.04120 0.0216 0.0147 1.0000 16.000 1.3690 0.04907 0.04475 0.0206 0.0147 1.0000 16.250 1.3649 0.05279 0.04858 0.0194 0.0146 1.0000 16.500 1.3591 0.05679 0.05269 0.0181 0.0146 1.0000 16.750 1.3516 0.06108 0.05710 0.0165 0.0145 1.0000 17.000 1.3430 0.06563 0.06177 0.0147 0.0145 1.0000 17.250 1.3328 0.07050 0.06676 0.0127 0.0145 1.0000 17.500 1.3216 0.07564 0.07202 0.0105 0.0145 1.0000 17.750 1.3091 0.08112 0.07761 0.0081 0.0144 1.0000 18.000 1.2956 0.08685 0.08346 0.0055 0.0144 1.0000 18.250 1.2810 0.09288 0.08962 0.0027 0.0144 1.0000 18.500 1.2649 0.09935 0.09622 -0.0005 0.0144 1.0000 18.750 1.2473 0.10621 0.10320 -0.0039 0.0144 1.0000 19.000 1.2286 0.11350 0.11062 -0.0076 0.0145 1.0000 19.250 1.2080 0.12137 0.11862 -0.0118 0.0145 1.0000