FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.43 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63120-il-1000000-n5.txt Download as CSV file: xf-fx63120-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-120 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8201 0.04631 0.04380 -0.0975 0.9960 0.0085
-13.750 -0.8337 0.03773 0.03500 -0.1087 0.9913 0.0086
-13.500 -0.8239 0.03178 0.02886 -0.1190 0.9866 0.0087
-13.250 -0.8054 0.02760 0.02450 -0.1272 0.9813 0.0089
-13.000 -0.7740 0.02441 0.02113 -0.1357 0.9777 0.0091
-12.750 -0.7404 0.02241 0.01897 -0.1412 0.9758 0.0094
-12.500 -0.7198 0.02107 0.01751 -0.1424 0.9685 0.0096
-12.000 -0.6663 0.01879 0.01498 -0.1458 0.9555 0.0100
-11.750 -0.6365 0.01776 0.01388 -0.1477 0.9485 0.0105
-11.500 -0.6018 0.01691 0.01296 -0.1502 0.9422 0.0108
-11.250 -0.5626 0.01619 0.01217 -0.1534 0.9372 0.0114
-11.000 -0.5197 0.01547 0.01135 -0.1573 0.9319 0.0119
-10.750 -0.4736 0.01474 0.01051 -0.1619 0.9267 0.0125
-10.500 -0.4296 0.01406 0.00972 -0.1660 0.9175 0.0130
-10.250 -0.3910 0.01365 0.00923 -0.1687 0.9049 0.0136
-10.000 -0.3586 0.01331 0.00878 -0.1701 0.8923 0.0141
-9.750 -0.3293 0.01299 0.00836 -0.1707 0.8807 0.0147
-9.500 -0.3007 0.01265 0.00792 -0.1712 0.8706 0.0152
-9.000 -0.2441 0.01199 0.00708 -0.1720 0.8521 0.0162
-8.500 -0.1877 0.01164 0.00664 -0.1724 0.8361 0.0173
-8.250 -0.1595 0.01144 0.00636 -0.1726 0.8279 0.0179
-8.000 -0.1309 0.01118 0.00603 -0.1729 0.8205 0.0185
-7.750 -0.1023 0.01095 0.00572 -0.1731 0.8132 0.0190
-7.500 -0.0736 0.01075 0.00546 -0.1734 0.8066 0.0194
-7.250 -0.0445 0.01042 0.00508 -0.1739 0.7991 0.0202
-7.000 -0.0158 0.01024 0.00485 -0.1741 0.7922 0.0207
-6.750 0.0133 0.01004 0.00461 -0.1745 0.7854 0.0213
-6.500 0.0421 0.00988 0.00439 -0.1747 0.7787 0.0220
-6.250 0.0713 0.00970 0.00416 -0.1750 0.7723 0.0226
-6.000 0.1005 0.00952 0.00392 -0.1753 0.7653 0.0231
-5.750 0.1296 0.00937 0.00371 -0.1756 0.7588 0.0235
-5.500 0.1595 0.00908 0.00337 -0.1762 0.7505 0.0243
-5.250 0.1888 0.00889 0.00312 -0.1765 0.7410 0.0250
-5.000 0.2178 0.00876 0.00292 -0.1767 0.7304 0.0256
-4.750 0.2472 0.00862 0.00273 -0.1771 0.7219 0.0263
-4.500 0.2765 0.00850 0.00256 -0.1774 0.7146 0.0270
-4.250 0.3061 0.00839 0.00241 -0.1777 0.7084 0.0278
-4.000 0.3355 0.00829 0.00227 -0.1780 0.7016 0.0284
-3.750 0.3649 0.00820 0.00213 -0.1782 0.6954 0.0289
-3.500 0.3949 0.00806 0.00197 -0.1787 0.6891 0.0302
-3.250 0.4242 0.00798 0.00185 -0.1789 0.6823 0.0314
-3.000 0.4538 0.00791 0.00176 -0.1792 0.6763 0.0327
-2.750 0.4831 0.00786 0.00168 -0.1795 0.6699 0.0343
-2.500 0.5123 0.00781 0.00161 -0.1797 0.6637 0.0378
-2.250 0.5421 0.00772 0.00155 -0.1801 0.6571 0.0491
-2.000 0.5717 0.00763 0.00151 -0.1804 0.6503 0.0717
-1.750 0.6017 0.00753 0.00146 -0.1809 0.6445 0.0994
-1.500 0.6324 0.00734 0.00142 -0.1816 0.6373 0.1621
-1.250 0.6641 0.00706 0.00138 -0.1827 0.6304 0.2660
-1.000 0.6948 0.00690 0.00143 -0.1834 0.6234 0.3525
-0.500 0.7521 0.00697 0.00149 -0.1836 0.6084 0.3825
-0.250 0.7804 0.00703 0.00153 -0.1836 0.6001 0.3950
0.000 0.8091 0.00706 0.00157 -0.1837 0.5917 0.4095
0.500 0.8651 0.00722 0.00169 -0.1837 0.5642 0.4368
1.000 0.9199 0.00750 0.00184 -0.1834 0.5280 0.4488
1.250 0.9474 0.00763 0.00192 -0.1833 0.5131 0.4557
1.500 0.9748 0.00777 0.00202 -0.1832 0.4974 0.4646
2.000 1.0294 0.00806 0.00226 -0.1830 0.4673 0.4940
2.250 1.0565 0.00823 0.00241 -0.1828 0.4510 0.5147
2.500 1.0833 0.00842 0.00257 -0.1826 0.4340 0.5358
2.750 1.1101 0.00862 0.00273 -0.1824 0.4192 0.5538
3.000 1.1369 0.00880 0.00290 -0.1822 0.4067 0.5688
3.250 1.1636 0.00899 0.00306 -0.1820 0.3933 0.5815
3.500 1.1897 0.00923 0.00325 -0.1817 0.3763 0.5929
3.750 1.2155 0.00949 0.00345 -0.1814 0.3576 0.6035
4.000 1.2407 0.00980 0.00367 -0.1809 0.3337 0.6127
4.250 1.2650 0.01019 0.00394 -0.1803 0.3066 0.6222
4.500 1.2896 0.01054 0.00421 -0.1798 0.2837 0.6313
4.750 1.3140 0.01090 0.00449 -0.1792 0.2637 0.6409
5.000 1.3377 0.01132 0.00482 -0.1785 0.2396 0.6498
5.250 1.3609 0.01178 0.00516 -0.1778 0.2170 0.6584
5.500 1.3849 0.01215 0.00548 -0.1771 0.2006 0.6670
6.000 1.4320 0.01293 0.00616 -0.1758 0.1694 0.6846
6.250 1.4549 0.01336 0.00653 -0.1750 0.1529 0.6946
6.500 1.4775 0.01381 0.00692 -0.1741 0.1371 0.7060
6.750 1.4991 0.01431 0.00736 -0.1732 0.1202 0.7163
7.000 1.5201 0.01485 0.00783 -0.1721 0.1043 0.7283
7.500 1.5632 0.01576 0.00872 -0.1701 0.0852 0.7543
7.750 1.5844 0.01621 0.00918 -0.1690 0.0786 0.7683
8.000 1.6060 0.01659 0.00961 -0.1681 0.0743 0.7854
8.250 1.6259 0.01707 0.01011 -0.1668 0.0687 0.8052
8.500 1.6464 0.01744 0.01056 -0.1656 0.0651 0.8338
8.750 1.6561 0.01763 0.01096 -0.1622 0.0613 1.0000
9.000 1.6713 0.01821 0.01152 -0.1601 0.0556 1.0000
9.250 1.6857 0.01883 0.01211 -0.1579 0.0495 1.0000
9.500 1.6999 0.01948 0.01274 -0.1558 0.0445 1.0000
9.750 1.7127 0.02022 0.01347 -0.1535 0.0398 1.0000
10.000 1.7271 0.02089 0.01415 -0.1515 0.0373 1.0000
10.250 1.7408 0.02161 0.01490 -0.1495 0.0353 1.0000
10.500 1.7531 0.02244 0.01574 -0.1473 0.0332 1.0000
10.750 1.7663 0.02324 0.01658 -0.1454 0.0318 1.0000
11.000 1.7795 0.02406 0.01745 -0.1435 0.0308 1.0000
11.250 1.7918 0.02497 0.01840 -0.1417 0.0297 1.0000
11.500 1.8025 0.02602 0.01949 -0.1397 0.0283 1.0000
11.750 1.8121 0.02720 0.02070 -0.1377 0.0268 1.0000
12.000 1.8235 0.02828 0.02184 -0.1360 0.0260 1.0000
12.250 1.8343 0.02943 0.02305 -0.1344 0.0249 1.0000
12.500 1.8439 0.03074 0.02440 -0.1328 0.0235 1.0000
12.750 1.8516 0.03226 0.02595 -0.1311 0.0220 1.0000
13.000 1.8603 0.03372 0.02747 -0.1295 0.0207 1.0000
13.250 1.8674 0.03539 0.02918 -0.1280 0.0187 1.0000
13.500 1.8730 0.03726 0.03108 -0.1265 0.0167 1.0000
13.750 1.8772 0.03933 0.03319 -0.1251 0.0146 1.0000
14.000 1.8808 0.04152 0.03544 -0.1238 0.0130 1.0000
14.250 1.8837 0.04388 0.03785 -0.1226 0.0117 1.0000
14.500 1.8861 0.04636 0.04040 -0.1215 0.0107 1.0000
14.750 1.8889 0.04887 0.04299 -0.1206 0.0100 1.0000
15.000 1.8902 0.05166 0.04584 -0.1197 0.0093 1.0000
15.250 1.8910 0.05459 0.04885 -0.1191 0.0088 1.0000
15.500 1.8920 0.05759 0.05194 -0.1186 0.0084 1.0000
15.750 1.8927 0.06069 0.05513 -0.1182 0.0080 1.0000
16.000 1.8925 0.06402 0.05855 -0.1180 0.0076 1.0000
16.250 1.8913 0.06758 0.06221 -0.1180 0.0073 1.0000
16.500 1.8892 0.07136 0.06608 -0.1181 0.0071 1.0000
16.750 1.8857 0.07545 0.07027 -0.1184 0.0068 1.0000
17.000 1.8804 0.07990 0.07482 -0.1189 0.0064 1.0000
17.250 1.8772 0.08414 0.07917 -0.1196 0.0063 1.0000
17.500 1.8734 0.08856 0.08370 -0.1205 0.0061 1.0000
17.750 1.8682 0.09329 0.08854 -0.1215 0.0059 1.0000
18.000 1.8628 0.09812 0.09347 -0.1228 0.0058 1.0000
18.250 1.8558 0.10331 0.09878 -0.1243 0.0056 1.0000
18.500 1.8484 0.10866 0.10424 -0.1260 0.0055 1.0000
18.750 1.8404 0.11416 0.10985 -0.1280 0.0053 1.0000
19.000 1.8311 0.11996 0.11575 -0.1303 0.0051 1.0000
19.250 1.8223 0.12571 0.12162 -0.1327 0.0050 1.0000
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