XFOIL Version 6.96 Calculated polar for: WORTMANN FX L V-152 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9371 0.16719 0.16355 0.0487 1.0005 0.0109 -18.250 -0.9634 0.15511 0.15133 0.0415 1.0005 0.0108 -18.000 -0.9840 0.14520 0.14127 0.0356 1.0005 0.0107 -17.750 -1.0030 0.13601 0.13195 0.0302 1.0005 0.0107 -17.500 -1.0211 0.12741 0.12320 0.0253 1.0005 0.0107 -17.250 -1.0384 0.11925 0.11489 0.0207 1.0005 0.0106 -17.000 -1.0548 0.11154 0.10703 0.0165 1.0005 0.0106 -16.750 -1.0697 0.10437 0.09970 0.0127 1.0005 0.0107 -16.500 -1.0831 0.09766 0.09283 0.0092 1.0005 0.0107 -16.250 -1.0949 0.09145 0.08647 0.0061 1.0005 0.0108 -16.000 -1.1051 0.08575 0.08062 0.0034 1.0005 0.0109 -15.750 -1.1138 0.08047 0.07519 0.0010 1.0005 0.0111 -15.500 -1.1210 0.07560 0.07017 -0.0011 1.0005 0.0113 -15.250 -1.1269 0.07110 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0.00468 -0.0017 0.6345 0.6358 0.250 0.0363 0.01250 0.00468 -0.0018 0.6305 0.6399 0.500 0.0650 0.01251 0.00468 -0.0020 0.6266 0.6439 0.750 0.0938 0.01250 0.00470 -0.0022 0.6215 0.6477 1.000 0.1226 0.01250 0.00468 -0.0025 0.6165 0.6514 1.250 0.1510 0.01246 0.00469 -0.0025 0.6120 0.6545 1.500 0.1794 0.01247 0.00472 -0.0026 0.6074 0.6581 1.750 0.2080 0.01246 0.00479 -0.0028 0.6015 0.6620 2.000 0.2365 0.01244 0.00478 -0.0029 0.5954 0.6658 2.250 0.2651 0.01244 0.00474 -0.0030 0.5897 0.6697 2.500 0.2933 0.01241 0.00484 -0.0030 0.5820 0.6729 2.750 0.3214 0.01240 0.00488 -0.0030 0.5754 0.6766 3.000 0.3496 0.01241 0.00493 -0.0030 0.5688 0.6806 3.250 0.3780 0.01241 0.00501 -0.0031 0.5597 0.6847 3.500 0.4061 0.01241 0.00502 -0.0031 0.5501 0.6885 3.750 0.4338 0.01237 0.00507 -0.0030 0.5363 0.6920 4.000 0.4616 0.01234 0.00513 -0.0030 0.5199 0.6961 4.250 0.4892 0.01232 0.00512 -0.0028 0.4988 0.7007 4.500 0.5163 0.01238 0.00511 -0.0027 0.4765 0.7060 4.750 0.5427 0.01248 0.00522 -0.0024 0.4494 0.7105 5.000 0.5686 0.01268 0.00535 -0.0021 0.4122 0.7158 5.250 0.5928 0.01308 0.00554 -0.0018 0.3587 0.7216 5.500 0.6157 0.01364 0.00588 -0.0013 0.3109 0.7272 5.750 0.6389 0.01419 0.00630 -0.0010 0.2656 0.7335 6.000 0.6611 0.01490 0.00679 -0.0006 0.2173 0.7405 6.250 0.6838 0.01550 0.00728 -0.0003 0.1805 0.7466 6.500 0.7067 0.01603 0.00777 0.0001 0.1600 0.7536 6.750 0.7300 0.01655 0.00828 0.0004 0.1420 0.7614 7.000 0.7528 0.01702 0.00878 0.0009 0.1232 0.7692 7.250 0.7752 0.01757 0.00930 0.0013 0.1056 0.7784 7.500 0.7967 0.01812 0.00985 0.0018 0.0902 0.7887 7.750 0.8181 0.01869 0.01042 0.0024 0.0786 0.8005 8.000 0.8393 0.01924 0.01101 0.0030 0.0707 0.8144 8.250 0.8601 0.01974 0.01161 0.0037 0.0646 0.8301 8.500 0.8806 0.02024 0.01221 0.0045 0.0585 0.8498 8.750 0.8995 0.02073 0.01283 0.0056 0.0528 0.8740 9.000 0.9190 0.02129 0.01350 0.0064 0.0482 0.9151 9.250 0.9445 0.02199 0.01426 0.0056 0.0439 0.9995 9.500 0.9626 0.02280 0.01507 0.0061 0.0402 0.9995 9.750 0.9794 0.02363 0.01593 0.0068 0.0366 0.9995 10.000 0.9951 0.02445 0.01680 0.0076 0.0332 0.9995 10.250 1.0104 0.02537 0.01776 0.0082 0.0302 0.9995 10.500 1.0249 0.02640 0.01883 0.0087 0.0279 0.9995 10.750 1.0386 0.02754 0.02001 0.0091 0.0263 0.9995 11.000 1.0516 0.02877 0.02129 0.0094 0.0251 0.9995 11.250 1.0636 0.03011 0.02269 0.0097 0.0241 0.9995 11.500 1.0739 0.03165 0.02426 0.0100 0.0230 0.9995 11.750 1.0841 0.03321 0.02591 0.0102 0.0217 0.9995 12.000 1.0924 0.03496 0.02774 0.0104 0.0207 0.9995 12.250 1.0993 0.03688 0.02973 0.0106 0.0199 0.9995 12.500 1.1070 0.03873 0.03171 0.0107 0.0190 0.9995 12.750 1.1125 0.04083 0.03391 0.0108 0.0180 0.9995 13.000 1.1159 0.04316 0.03633 0.0107 0.0173 0.9995 13.250 1.1218 0.04526 0.03859 0.0107 0.0163 0.9995 13.500 1.1251 0.04767 0.04113 0.0106 0.0155 0.9995 13.750 1.1265 0.05031 0.04388 0.0103 0.0148 0.9995 14.000 1.1282 0.05297 0.04669 0.0100 0.0141 0.9995 14.250 1.1282 0.05588 0.04975 0.0096 0.0134 0.9995 14.500 1.1266 0.05903 0.05303 0.0090 0.0129 0.9995 14.750 1.1243 0.06240 0.05653 0.0081 0.0125 0.9995 15.000 1.1209 0.06607 0.06032 0.0070 0.0121 0.9995 15.250 1.1159 0.07011 0.06451 0.0057 0.0118 0.9995 15.500 1.1098 0.07446 0.06901 0.0041 0.0116 0.9995 15.750 1.1024 0.07914 0.07383 0.0022 0.0114 0.9995 16.000 1.0937 0.08422 0.07906 0.0001 0.0112 0.9995 16.250 1.0834 0.08971 0.08469 -0.0024 0.0111 0.9995 16.500 1.0717 0.09562 0.09074 -0.0052 0.0110 0.9995 16.750 1.0584 0.10204 0.09731 -0.0083 0.0109 0.9995 17.000 1.0436 0.10886 0.10429 -0.0118 0.0109 0.9995 17.250 1.0274 0.11621 0.11178 -0.0156 0.0109 0.9995 17.500 1.0101 0.12398 0.11970 -0.0198 0.0109 0.9995 17.750 0.9919 0.13219 0.12805 -0.0242 0.0109 0.9995 18.000 0.9731 0.14087 0.13687 -0.0291 0.0110 0.9995 18.250 0.9530 0.15019 0.14632 -0.0344 0.0110 0.9995 18.500 0.9294 0.16084 0.15711 -0.0406 0.0111 0.9995