XFOIL Version 6.96 Calculated polar for: FX 71-L-150/20 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 -1.0823 0.13443 0.13142 0.0159 1.0000 0.0092 -19.500 -1.0944 0.12771 0.12459 0.0120 1.0000 0.0091 -19.250 -1.1058 0.12122 0.11799 0.0083 1.0000 0.0091 -19.000 -1.1160 0.11510 0.11176 0.0048 1.0000 0.0091 -18.750 -1.1256 0.10923 0.10580 0.0016 1.0000 0.0091 -18.500 -1.1339 0.10373 0.10021 -0.0013 1.0000 0.0091 -18.250 -1.1431 0.09821 0.09458 -0.0041 1.0000 0.0091 -18.000 -1.1516 0.09294 0.08921 -0.0066 1.0000 0.0091 -17.750 -1.1589 0.08801 0.08418 -0.0090 1.0000 0.0091 -17.500 -1.1651 0.08333 0.07941 -0.0111 1.0000 0.0091 -17.250 -1.1710 0.07884 0.07482 -0.0130 1.0000 0.0091 -17.000 -1.1755 0.07465 0.07054 -0.0147 1.0000 0.0091 -16.750 -1.1788 0.07072 0.06653 -0.0163 1.0000 0.0092 -16.500 -1.1822 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0.6134 3.250 0.3530 0.00995 0.00281 0.0011 0.0297 0.6164 3.500 0.3807 0.01012 0.00296 0.0011 0.0253 0.6191 3.750 0.4081 0.01035 0.00313 0.0012 0.0146 0.6217 4.000 0.4357 0.01054 0.00330 0.0012 0.0131 0.6239 4.250 0.4633 0.01071 0.00347 0.0013 0.0125 0.6263 4.500 0.4906 0.01088 0.00366 0.0014 0.0122 0.6301 4.750 0.5178 0.01107 0.00387 0.0015 0.0119 0.6340 5.000 0.5448 0.01127 0.00409 0.0016 0.0116 0.6377 5.250 0.5717 0.01150 0.00432 0.0018 0.0113 0.6412 5.500 0.5982 0.01176 0.00460 0.0020 0.0110 0.6439 5.750 0.6246 0.01203 0.00487 0.0022 0.0108 0.6460 6.000 0.6506 0.01231 0.00518 0.0024 0.0106 0.6490 6.250 0.6765 0.01257 0.00547 0.0027 0.0105 0.6520 6.500 0.7022 0.01285 0.00577 0.0030 0.0104 0.6551 6.750 0.7276 0.01315 0.00610 0.0033 0.0104 0.6581 7.000 0.7526 0.01347 0.00644 0.0037 0.0103 0.6612 7.250 0.7774 0.01381 0.00680 0.0040 0.0102 0.6643 7.750 0.8253 0.01456 0.00760 0.0050 0.0100 0.6713 8.000 0.8486 0.01494 0.00802 0.0056 0.0100 0.6754 8.250 0.8712 0.01536 0.00848 0.0062 0.0099 0.6792 8.500 0.8932 0.01581 0.00896 0.0069 0.0099 0.6827 8.750 0.9146 0.01627 0.00946 0.0077 0.0099 0.6861 9.000 0.9349 0.01677 0.00999 0.0086 0.0098 0.6898 9.250 0.9542 0.01728 0.01056 0.0096 0.0098 0.6942 9.500 0.9722 0.01783 0.01116 0.0108 0.0098 0.6987 9.750 0.9890 0.01840 0.01177 0.0121 0.0097 0.7028 10.000 1.0020 0.01901 0.01243 0.0140 0.0097 0.7066 10.250 1.0114 0.01962 0.01309 0.0164 0.0097 0.7105 10.500 1.0191 0.02040 0.01393 0.0186 0.0096 0.7152 10.750 1.0271 0.02135 0.01493 0.0202 0.0096 0.7201 11.000 1.0368 0.02231 0.01595 0.0216 0.0095 0.7248 11.500 1.0558 0.02440 0.01815 0.0241 0.0094 0.7341 11.750 1.0641 0.02559 0.01941 0.0253 0.0094 0.7394 12.000 1.0738 0.02672 0.02059 0.0263 0.0094 0.7447 12.500 1.0891 0.02937 0.02338 0.0282 0.0093 0.7558 12.750 1.0958 0.03084 0.02492 0.0291 0.0093 0.7622 13.000 1.1031 0.03231 0.02645 0.0298 0.0093 0.7686 13.250 1.1098 0.03382 0.02804 0.0305 0.0093 0.7767 13.500 1.1169 0.03537 0.02966 0.0310 0.0093 0.7841 13.750 1.1195 0.03733 0.03172 0.0315 0.0093 0.7905 14.000 1.1263 0.03898 0.03344 0.0319 0.0092 0.7976 14.250 1.1286 0.04112 0.03566 0.0322 0.0092 0.8037 14.500 1.1335 0.04301 0.03764 0.0323 0.0092 0.8107 14.750 1.1375 0.04505 0.03978 0.0324 0.0092 0.8194 15.000 1.1379 0.04747 0.04234 0.0324 0.0092 0.8344 15.250 1.1522 0.04992 0.04517 0.0297 0.0092 0.9248 15.500 1.1840 0.05396 0.04935 0.0216 0.0091 0.9994 15.750 1.1845 0.05707 0.05255 0.0206 0.0092 1.0000 16.000 1.1851 0.06016 0.05571 0.0197 0.0092 1.0000 16.250 1.1851 0.06339 0.05902 0.0186 0.0091 1.0000 16.500 1.1827 0.06698 0.06270 0.0174 0.0091 1.0000 16.750 1.1803 0.07071 0.06651 0.0161 0.0091 1.0000 17.000 1.1779 0.07453 0.07041 0.0145 0.0091 1.0000 17.250 1.1733 0.07873 0.07470 0.0128 0.0091 1.0000 17.500 1.1674 0.08321 0.07929 0.0109 0.0091 1.0000 17.750 1.1610 0.08792 0.08409 0.0087 0.0091 1.0000 18.000 1.1542 0.09279 0.08904 0.0064 0.0091 1.0000 18.250 1.1464 0.09794 0.09429 0.0039 0.0091 1.0000 18.500 1.1372 0.10344 0.09990 0.0011 0.0091 1.0000 18.750 1.1278 0.10911 0.10567 -0.0018 0.0091 1.0000 19.000 1.1175 0.11510 0.11176 -0.0051 0.0091 1.0000 19.250 1.1069 0.12130 0.11807 -0.0085 0.0091 1.0000