XFOIL Version 6.96 Calculated polar for: NPL 9510 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1438 0.12886 0.12607 -0.0083 1.0000 0.0159 -19.500 -1.1563 0.12248 0.11959 -0.0118 1.0000 0.0160 -19.250 -1.1681 0.11632 0.11333 -0.0150 1.0000 0.0161 -19.000 -1.1795 0.11037 0.10729 -0.0182 1.0000 0.0162 -18.750 -1.1903 0.10464 0.10146 -0.0211 1.0000 0.0163 -18.500 -1.2001 0.09911 0.09584 -0.0239 1.0000 0.0164 -18.250 -1.2093 0.09381 0.09045 -0.0265 1.0000 0.0164 -18.000 -1.2176 0.08879 0.08533 -0.0290 1.0000 0.0165 -17.750 -1.2248 0.08396 0.08041 -0.0313 1.0000 0.0166 -17.500 -1.2310 0.07940 0.07576 -0.0334 1.0000 0.0168 -17.250 -1.2364 0.07509 0.07135 -0.0354 1.0000 0.0169 -17.000 -1.2405 0.07099 0.06716 -0.0373 1.0000 0.0170 -16.750 -1.2437 0.06711 0.06319 -0.0389 1.0000 0.0171 -16.500 -1.2461 0.06345 0.05944 -0.0405 1.0000 0.0173 -16.250 -1.2473 0.05998 0.05587 -0.0419 1.0000 0.0174 -16.000 -1.2477 0.05672 0.05253 -0.0432 1.0000 0.0175 -15.750 -1.2467 0.05369 0.04941 -0.0444 1.0000 0.0177 -15.500 -1.2445 0.05088 0.04652 -0.0454 1.0000 0.0178 -15.250 -1.2413 0.04831 0.04386 -0.0463 1.0000 0.0179 -15.000 -1.2372 0.04590 0.04137 -0.0471 1.0000 0.0180 -14.750 -1.2406 0.04285 0.03824 -0.0476 1.0000 0.0183 -14.500 -1.2438 0.03984 0.03516 -0.0482 1.0000 0.0186 -14.250 -1.2420 0.03734 0.03260 -0.0488 1.0000 0.0188 -14.000 -1.2373 0.03516 0.03037 -0.0493 1.0000 0.0191 -13.750 -1.2304 0.03321 0.02836 -0.0497 1.0000 0.0193 -13.500 -1.2226 0.03139 0.02650 -0.0500 1.0000 0.0196 -13.250 -1.2147 0.02965 0.02471 -0.0502 1.0000 0.0198 -13.000 -1.2077 0.02799 0.02299 -0.0501 1.0000 0.0200 -12.750 -1.2048 0.02644 0.02139 -0.0490 1.0000 0.0203 -12.500 -1.2005 0.02498 0.01988 -0.0481 1.0000 0.0205 -12.250 -1.1911 0.02363 0.01847 -0.0479 1.0000 0.0208 -12.000 -1.1781 0.02243 0.01721 -0.0480 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0.00616 0.00222 -0.0931 0.9743 0.4880 -2.250 0.0080 0.00607 0.00216 -0.0944 0.9728 0.4936 -2.000 0.0374 0.00598 0.00210 -0.0944 0.9673 0.5013 -1.750 0.0649 0.00581 0.00192 -0.0936 0.9562 0.5085 -1.500 0.0896 0.00568 0.00181 -0.0923 0.9432 0.5146 -1.250 0.1163 0.00564 0.00177 -0.0917 0.9320 0.5201 -1.000 0.1438 0.00561 0.00172 -0.0912 0.9195 0.5245 -0.750 0.1708 0.00556 0.00166 -0.0907 0.9003 0.5287 -0.500 0.1976 0.00559 0.00161 -0.0900 0.8684 0.5323 -0.250 0.2222 0.00585 0.00157 -0.0888 0.7862 0.5359 0.000 0.2331 0.00827 0.00200 -0.0860 0.2712 0.5387 0.250 0.2583 0.00898 0.00216 -0.0856 0.1185 0.5421 0.500 0.2855 0.00936 0.00231 -0.0855 0.0607 0.5459 0.750 0.3138 0.00954 0.00246 -0.0854 0.0506 0.5494 1.000 0.3421 0.00974 0.00262 -0.0854 0.0454 0.5529 1.250 0.3705 0.00992 0.00278 -0.0853 0.0428 0.5561 1.500 0.3989 0.01006 0.00292 -0.0853 0.0405 0.5596 1.750 0.4266 0.01033 0.00321 -0.0851 0.0380 0.5633 2.000 0.4550 0.01049 0.00338 -0.0850 0.0369 0.5668 2.250 0.4831 0.01067 0.00357 -0.0849 0.0356 0.5702 2.500 0.5111 0.01087 0.00375 -0.0848 0.0342 0.5732 2.750 0.5380 0.01127 0.00415 -0.0845 0.0326 0.5768 3.000 0.5659 0.01147 0.00438 -0.0844 0.0319 0.5805 3.250 0.5937 0.01169 0.00463 -0.0842 0.0310 0.5840 3.500 0.6213 0.01194 0.00489 -0.0840 0.0301 0.5873 3.750 0.6489 0.01218 0.00512 -0.0838 0.0291 0.5905 4.000 0.6750 0.01270 0.00563 -0.0834 0.0279 0.5941 4.250 0.7021 0.01301 0.00600 -0.0831 0.0273 0.5980 4.500 0.7295 0.01328 0.00632 -0.0828 0.0266 0.6017 4.750 0.7566 0.01360 0.00666 -0.0825 0.0258 0.6053 5.000 0.7836 0.01392 0.00698 -0.0823 0.0252 0.6085 5.250 0.8105 0.01423 0.00731 -0.0820 0.0245 0.6125 5.500 0.8358 0.01494 0.00805 -0.0814 0.0237 0.6165 5.750 0.8618 0.01553 0.00871 -0.0809 0.0232 0.6206 6.000 0.8887 0.01584 0.00907 -0.0806 0.0227 0.6244 6.250 0.9153 0.01620 0.00949 -0.0802 0.0221 0.6281 6.500 0.9417 0.01659 0.00994 -0.0798 0.0216 0.6325 6.750 0.9679 0.01698 0.01038 -0.0794 0.0211 0.6371 7.000 0.9940 0.01739 0.01081 -0.0790 0.0207 0.6416 7.250 1.0193 0.01794 0.01139 -0.0785 0.0203 0.6459 7.500 1.0420 0.01936 0.01295 -0.0776 0.0198 0.6504 7.750 1.0674 0.01985 0.01356 -0.0770 0.0195 0.6554 8.000 1.0921 0.02052 0.01434 -0.0764 0.0192 0.6603 8.250 1.1162 0.02131 0.01527 -0.0756 0.0189 0.6656 8.500 1.1396 0.02216 0.01626 -0.0748 0.0185 0.6711 8.750 1.1627 0.02301 0.01723 -0.0740 0.0182 0.6766 9.000 1.1854 0.02387 0.01821 -0.0731 0.0180 0.6821 9.250 1.2078 0.02466 0.01913 -0.0722 0.0177 0.6884 9.500 1.2297 0.02547 0.02004 -0.0712 0.0175 0.6948 9.750 1.2516 0.02617 0.02083 -0.0702 0.0173 0.7011 10.000 1.2729 0.02688 0.02161 -0.0692 0.0171 0.7079 10.250 1.2912 0.02812 0.02296 -0.0679 0.0168 0.7143 10.500 1.2972 0.03143 0.02669 -0.0650 0.0165 0.7205 10.750 1.3115 0.03302 0.02850 -0.0631 0.0164 0.7279 11.000 1.3199 0.03537 0.03117 -0.0606 0.0162 0.7346 11.250 1.3151 0.03933 0.03557 -0.0568 0.0160 0.7413 11.500 0.6645 0.13141 0.12928 -0.0649 0.0204 0.6747