XFOIL Version 6.96 Calculated polar for: NPL 9627 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4870 0.10002 0.09646 -0.0172 1.0000 0.0797 -10.500 -0.7630 0.04768 0.04317 -0.0451 1.0000 0.0395 -10.250 -0.8780 0.04907 0.04347 -0.0351 1.0000 0.0354 -10.000 -0.8690 0.04571 0.04002 -0.0339 1.0000 0.0350 -9.750 -0.8651 0.04235 0.03639 -0.0320 1.0000 0.0344 -9.500 -0.8609 0.03902 0.03270 -0.0297 1.0000 0.0339 -9.250 -0.8533 0.03603 0.02933 -0.0274 1.0000 0.0337 -9.000 -0.8420 0.03347 0.02642 -0.0252 1.0000 0.0339 -8.750 -0.8286 0.03124 0.02383 -0.0232 1.0000 0.0344 -8.500 -0.8141 0.02932 0.02150 -0.0210 1.0000 0.0353 -8.250 -0.7963 0.02738 0.01937 -0.0194 1.0000 0.0363 -8.000 -0.7759 0.02605 0.01808 -0.0183 1.0000 0.0377 -7.750 -0.7566 0.02483 0.01670 -0.0168 1.0000 0.0393 -7.500 -0.7372 0.02367 0.01531 -0.0152 1.0000 0.0408 -7.250 -0.7171 0.02249 0.01423 -0.0140 1.0000 0.0428 -7.000 -0.6978 0.02191 0.01350 -0.0125 1.0000 0.0458 -6.750 -0.6786 0.02078 0.01251 -0.0112 1.0000 0.0487 -6.500 -0.6589 0.02004 0.01169 -0.0096 1.0000 0.0515 -6.250 -0.6409 0.01894 0.01069 -0.0079 1.0000 0.0542 -6.000 -0.6223 0.01820 0.00995 -0.0062 1.0000 0.0573 -5.750 -0.6048 0.01734 0.00912 -0.0044 1.0000 0.0604 -5.500 -0.5867 0.01668 0.00849 -0.0028 1.0000 0.0642 -5.250 -0.5684 0.01603 0.00784 -0.0011 1.0000 0.0684 -5.000 -0.5491 0.01552 0.00734 0.0003 1.0000 0.0741 -4.750 -0.5297 0.01497 0.00684 0.0016 1.0000 0.0827 -4.500 -0.5102 0.01430 0.00636 0.0029 1.0000 0.1043 -4.250 -0.4921 0.01303 0.00592 0.0038 1.0000 0.2386 -4.000 -0.4713 0.01266 0.00584 0.0047 1.0000 0.3104 -3.750 -0.4369 0.01245 0.00579 0.0029 0.9964 0.3605 -3.500 -0.3932 0.01226 0.00569 -0.0006 0.9901 0.4021 -3.250 -0.3511 0.01198 0.00557 -0.0037 0.9830 0.4446 -3.000 -0.3105 0.01170 0.00544 -0.0064 0.9756 0.4861 -2.750 -0.2690 0.01135 0.00530 -0.0093 0.9686 0.5308 -2.500 -0.2313 0.01097 0.00519 -0.0112 0.9601 0.5865 -2.250 -0.1906 0.01058 0.00511 -0.0135 0.9535 0.6539 -2.000 -0.1563 0.01027 0.00506 -0.0142 0.9433 0.7172 -1.750 -0.1184 0.01003 0.00501 -0.0154 0.9357 0.7743 -1.500 -0.0878 0.00992 0.00501 -0.0149 0.9223 0.8185 -1.250 -0.0566 0.00987 0.00500 -0.0144 0.9081 0.8539 -1.000 -0.0266 0.00986 0.00498 -0.0137 0.8927 0.8835 -0.750 0.0063 0.00992 0.00500 -0.0136 0.8767 0.9047 -0.500 0.0398 0.01000 0.00502 -0.0136 0.8593 0.9228 -0.250 0.0748 0.01011 0.00504 -0.0142 0.8401 0.9380 0.000 0.1113 0.01022 0.00504 -0.0151 0.8194 0.9515 0.250 0.1579 0.01032 0.00502 -0.0183 0.7980 0.9593 0.750 0.2410 0.01051 0.00498 -0.0232 0.7539 0.9791 1.000 0.2859 0.01055 0.00489 -0.0266 0.7294 0.9867 1.250 0.3288 0.01061 0.00479 -0.0295 0.7053 0.9946 1.500 0.3686 0.01062 0.00470 -0.0321 0.6792 1.0000 1.750 0.3921 0.01065 0.00461 -0.0313 0.6564 1.0000 2.000 0.4158 0.01070 0.00454 -0.0306 0.6348 1.0000 2.250 0.4396 0.01075 0.00450 -0.0299 0.6126 1.0000 2.500 0.4635 0.01082 0.00449 -0.0292 0.5909 1.0000 2.750 0.4871 0.01091 0.00450 -0.0284 0.5694 1.0000 3.000 0.5102 0.01102 0.00451 -0.0275 0.5463 1.0000 3.250 0.5331 0.01114 0.00454 -0.0266 0.5221 1.0000 3.500 0.5560 0.01127 0.00461 -0.0257 0.4987 1.0000 3.750 0.5787 0.01143 0.00469 -0.0247 0.4757 1.0000 4.000 0.6012 0.01159 0.00479 -0.0237 0.4514 1.0000 4.250 0.6234 0.01179 0.00491 -0.0226 0.4255 1.0000 4.500 0.6452 0.01203 0.00506 -0.0215 0.3979 1.0000 4.750 0.6665 0.01231 0.00523 -0.0203 0.3661 1.0000 5.000 0.6870 0.01266 0.00544 -0.0189 0.3282 1.0000 5.250 0.7061 0.01316 0.00571 -0.0175 0.2806 1.0000 5.500 0.7226 0.01395 0.00614 -0.0157 0.2129 1.0000 5.750 0.7387 0.01487 0.00671 -0.0138 0.1638 1.0000 6.000 0.7568 0.01558 0.00727 -0.0122 0.1460 1.0000 6.250 0.7758 0.01620 0.00782 -0.0107 0.1357 1.0000 6.500 0.7943 0.01687 0.00839 -0.0091 0.1277 1.0000 6.750 0.8149 0.01737 0.00892 -0.0078 0.1214 1.0000 7.000 0.8345 0.01799 0.00949 -0.0065 0.1160 1.0000 7.250 0.8541 0.01870 0.01018 -0.0052 0.1117 1.0000 7.500 0.8751 0.01926 0.01079 -0.0040 0.1074 1.0000 7.750 0.8952 0.02000 0.01148 -0.0029 0.1035 1.0000 8.000 0.9156 0.02090 0.01237 -0.0017 0.1000 1.0000 8.250 0.9370 0.02156 0.01311 -0.0007 0.0963 1.0000 8.500 0.9578 0.02236 0.01388 0.0002 0.0925 1.0000 8.750 0.9789 0.02352 0.01502 0.0011 0.0890 1.0000 9.000 0.9999 0.02430 0.01592 0.0021 0.0854 1.0000 9.250 1.0213 0.02525 0.01686 0.0029 0.0823 1.0000 9.500 1.0442 0.02690 0.01847 0.0033 0.0795 1.0000 9.750 1.0639 0.02784 0.01961 0.0044 0.0770 1.0000 10.000 1.0841 0.02888 0.02076 0.0054 0.0744 1.0000 10.250 1.1055 0.03005 0.02192 0.0060 0.0722 1.0000 10.500 1.1277 0.03218 0.02408 0.0062 0.0702 1.0000 10.750 1.1427 0.03333 0.02553 0.0079 0.0686 1.0000 11.000 1.1585 0.03467 0.02708 0.0092 0.0667 1.0000 11.250 1.1760 0.03594 0.02845 0.0102 0.0650 1.0000 11.500 1.1937 0.03733 0.02987 0.0111 0.0634 1.0000 11.750 1.2115 0.03996 0.03254 0.0115 0.0619 1.0000 12.000 1.2143 0.04150 0.03448 0.0142 0.0609 1.0000 12.250 1.2163 0.04350 0.03681 0.0167 0.0598 1.0000 12.500 1.2174 0.04556 0.03913 0.0190 0.0587 1.0000 12.750 1.2170 0.04744 0.04120 0.0215 0.0577 1.0000 13.000 1.2221 0.04902 0.04286 0.0233 0.0567 1.0000 13.250 1.2378 0.05034 0.04414 0.0239 0.0555 1.0000 13.500 1.2421 0.05339 0.04724 0.0249 0.0546 1.0000 13.750 1.2198 0.05624 0.05040 0.0276 0.0543 1.0000 14.000 1.1957 0.05994 0.05440 0.0289 0.0540 1.0000 14.250 1.1695 0.06453 0.05927 0.0287 0.0539 1.0000 14.500 1.1411 0.07013 0.06514 0.0271 0.0538 1.0000 14.750 1.1099 0.07690 0.07214 0.0239 0.0539 1.0000 15.000 1.0758 0.08495 0.08041 0.0194 0.0541 1.0000 15.250 1.0397 0.09430 0.08993 0.0138 0.0543 1.0000