XFOIL Version 6.96 Calculated polar for: FX 71-L-150/25 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0851 0.12879 0.12564 0.0076 1.0000 0.0091 -19.500 -1.0965 0.12246 0.11920 0.0040 1.0000 0.0091 -19.250 -1.1068 0.11635 0.11299 0.0007 1.0000 0.0091 -19.000 -1.1155 0.11073 0.10729 -0.0024 1.0000 0.0092 -18.750 -1.1253 0.10502 0.10147 -0.0054 1.0000 0.0091 -18.500 -1.1346 0.09953 0.09589 -0.0081 1.0000 0.0092 -18.250 -1.1432 0.09427 0.09052 -0.0107 1.0000 0.0091 -18.000 -1.1514 0.08921 0.08536 -0.0131 1.0000 0.0091 -17.750 -1.1571 0.08461 0.08068 -0.0152 1.0000 0.0091 -17.500 -1.1641 0.07995 0.07593 -0.0172 1.0000 0.0092 -17.250 -1.1687 0.07573 0.07162 -0.0190 1.0000 0.0092 -17.000 -1.1735 0.07162 0.06742 -0.0206 1.0000 0.0092 -16.750 -1.1768 0.06777 0.06348 -0.0221 1.0000 0.0092 -16.500 -1.1791 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0.6290 3.000 0.3244 0.00909 0.00236 0.0014 0.1131 0.6339 3.250 0.3505 0.00942 0.00256 0.0016 0.0814 0.6387 3.500 0.3764 0.00979 0.00278 0.0019 0.0495 0.6432 3.750 0.4025 0.01009 0.00300 0.0021 0.0289 0.6478 4.000 0.4296 0.01027 0.00317 0.0022 0.0240 0.6534 4.250 0.4562 0.01052 0.00338 0.0024 0.0141 0.6592 4.500 0.4833 0.01071 0.00356 0.0026 0.0131 0.6639 4.750 0.5102 0.01089 0.00376 0.0027 0.0126 0.6681 5.000 0.5369 0.01109 0.00397 0.0029 0.0122 0.6726 5.250 0.5636 0.01130 0.00420 0.0031 0.0119 0.6771 5.500 0.5899 0.01154 0.00445 0.0033 0.0115 0.6810 5.750 0.6162 0.01179 0.00470 0.0036 0.0113 0.6841 6.000 0.6417 0.01206 0.00501 0.0039 0.0110 0.6875 6.250 0.6672 0.01233 0.00530 0.0043 0.0109 0.6910 6.500 0.6926 0.01260 0.00559 0.0046 0.0108 0.6946 6.750 0.7178 0.01289 0.00590 0.0050 0.0107 0.6984 7.000 0.7426 0.01320 0.00622 0.0054 0.0106 0.7018 7.250 0.7670 0.01353 0.00657 0.0059 0.0105 0.7046 7.500 0.7909 0.01386 0.00693 0.0064 0.0105 0.7077 7.750 0.8143 0.01421 0.00731 0.0070 0.0104 0.7108 8.000 0.8372 0.01459 0.00772 0.0077 0.0103 0.7140 8.250 0.8597 0.01498 0.00814 0.0084 0.0103 0.7171 8.500 0.8814 0.01540 0.00859 0.0092 0.0102 0.7199 8.750 0.9025 0.01585 0.00906 0.0101 0.0102 0.7226 9.000 0.9229 0.01627 0.00952 0.0111 0.0101 0.7259 9.250 0.9420 0.01675 0.01004 0.0122 0.0100 0.7293 9.500 0.9600 0.01725 0.01059 0.0135 0.0100 0.7328 9.750 0.9769 0.01776 0.01113 0.0149 0.0098 0.7363 10.000 0.9893 0.01827 0.01168 0.0171 0.0098 0.7396 10.250 0.9991 0.01888 0.01234 0.0195 0.0098 0.7427 10.500 1.0089 0.01955 0.01306 0.0217 0.0098 0.7459 10.750 1.0177 0.02036 0.01393 0.0237 0.0097 0.7495 11.000 1.0280 0.02122 0.01483 0.0253 0.0097 0.7532 11.250 1.0376 0.02220 0.01586 0.0267 0.0097 0.7568 11.500 1.0478 0.02318 0.01689 0.0279 0.0096 0.7600 11.750 1.0561 0.02430 0.01808 0.0293 0.0096 0.7635 12.000 1.0663 0.02534 0.01917 0.0304 0.0096 0.7669 12.250 1.0749 0.02655 0.02042 0.0315 0.0095 0.7699 12.500 1.0819 0.02791 0.02183 0.0326 0.0096 0.7725 12.750 1.0922 0.02905 0.02302 0.0334 0.0095 0.7749 13.000 1.0993 0.03043 0.02448 0.0343 0.0095 0.7777 13.250 1.1048 0.03200 0.02612 0.0352 0.0094 0.7807 13.500 1.1106 0.03359 0.02778 0.0359 0.0095 0.7837 13.750 1.1170 0.03519 0.02944 0.0364 0.0094 0.7866 14.000 1.1217 0.03701 0.03133 0.0369 0.0094 0.7893 14.250 1.1263 0.03884 0.03324 0.0372 0.0094 0.7931 14.500 1.1306 0.04077 0.03525 0.0375 0.0093 0.7973 14.750 1.1333 0.04291 0.03749 0.0376 0.0093 0.8018 15.250 1.1384 0.04736 0.04217 0.0376 0.0093 0.8220 15.500 1.1417 0.04979 0.04500 0.0369 0.0093 0.9174 15.750 1.1827 0.05422 0.04960 0.0263 0.0092 0.9987 16.000 1.1843 0.05731 0.05278 0.0252 0.0092 1.0000 16.250 1.1838 0.06053 0.05608 0.0242 0.0092 1.0000 16.500 1.1820 0.06399 0.05962 0.0231 0.0092 1.0000 16.750 1.1808 0.06749 0.06319 0.0218 0.0092 1.0000 17.000 1.1762 0.07150 0.06729 0.0203 0.0092 1.0000 17.250 1.1710 0.07566 0.07155 0.0187 0.0092 1.0000 17.500 1.1662 0.07991 0.07588 0.0169 0.0091 1.0000 17.750 1.1605 0.08441 0.08048 0.0149 0.0091 1.0000 18.000 1.1534 0.08917 0.08533 0.0128 0.0092 1.0000 18.250 1.1460 0.09413 0.09039 0.0104 0.0092 1.0000 18.500 1.1376 0.09935 0.09570 0.0079 0.0091 1.0000 18.750 1.1288 0.10479 0.10123 0.0051 0.0091 1.0000 19.000 1.1197 0.11031 0.10684 0.0023 0.0091 1.0000 19.250 1.1098 0.11615 0.11277 -0.0009 0.0091 1.0000