FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 500,000 Max Cl/Cd: 114.73 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63120-il-500000-n5.txt Download as CSV file: xf-fx63120-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3379 0.12513 0.12268 -0.0400 1.0000 0.0101
-11.250 -0.5855 0.03797 0.03502 -0.1095 0.9707 0.0130
-11.000 -0.5709 0.03185 0.02864 -0.1214 0.9562 0.0131
-10.750 -0.5438 0.02937 0.02603 -0.1276 0.9461 0.0134
-10.500 -0.5116 0.02729 0.02377 -0.1329 0.9402 0.0137
-10.250 -0.4803 0.02530 0.02158 -0.1373 0.9327 0.0142
-10.000 -0.4435 0.02270 0.01862 -0.1431 0.9278 0.0150
-9.750 -0.4042 0.02033 0.01584 -0.1484 0.9232 0.0158
-9.500 -0.3630 0.01970 0.01517 -0.1522 0.9185 0.0163
-9.250 -0.3209 0.01918 0.01458 -0.1559 0.9135 0.0168
-9.000 -0.2805 0.01844 0.01369 -0.1595 0.9071 0.0176
-8.750 -0.2430 0.01741 0.01243 -0.1625 0.8991 0.0185
-8.500 -0.2078 0.01643 0.01118 -0.1649 0.8907 0.0193
-8.250 -0.1757 0.01577 0.01041 -0.1665 0.8812 0.0199
-8.000 -0.1450 0.01542 0.00999 -0.1675 0.8724 0.0205
-7.750 -0.1151 0.01505 0.00953 -0.1683 0.8638 0.0213
-7.500 -0.0858 0.01457 0.00891 -0.1689 0.8559 0.0221
-7.250 -0.0567 0.01407 0.00826 -0.1695 0.8475 0.0229
-7.000 -0.0276 0.01372 0.00777 -0.1699 0.8400 0.0236
-6.750 0.0011 0.01309 0.00709 -0.1706 0.8325 0.0244
-6.500 0.0302 0.01273 0.00667 -0.1711 0.8256 0.0252
-6.250 0.0591 0.01236 0.00623 -0.1715 0.8181 0.0259
-6.000 0.0884 0.01204 0.00583 -0.1719 0.8111 0.0268
-5.750 0.1175 0.01173 0.00545 -0.1723 0.8043 0.0278
-5.500 0.1468 0.01145 0.00508 -0.1727 0.7974 0.0284
-5.250 0.1768 0.01106 0.00462 -0.1734 0.7909 0.0291
-5.000 0.2069 0.01068 0.00421 -0.1740 0.7839 0.0301
-4.750 0.2367 0.01045 0.00391 -0.1745 0.7772 0.0312
-4.500 0.2661 0.01023 0.00365 -0.1749 0.7684 0.0323
-4.250 0.2955 0.01005 0.00339 -0.1753 0.7592 0.0333
-4.000 0.3248 0.00989 0.00315 -0.1756 0.7496 0.0342
-3.750 0.3546 0.00972 0.00292 -0.1760 0.7425 0.0353
-3.500 0.3845 0.00955 0.00272 -0.1764 0.7355 0.0373
-3.250 0.4140 0.00945 0.00257 -0.1767 0.7290 0.0399
-3.000 0.4437 0.00933 0.00243 -0.1771 0.7222 0.0433
-2.750 0.4732 0.00922 0.00232 -0.1774 0.7155 0.0520
-2.500 0.5032 0.00909 0.00222 -0.1779 0.7092 0.0725
-2.250 0.5335 0.00890 0.00213 -0.1785 0.7023 0.1078
-2.000 0.5652 0.00857 0.00203 -0.1796 0.6960 0.2007
-1.750 0.5974 0.00822 0.00201 -0.1809 0.6894 0.3216
-1.500 0.6264 0.00821 0.00205 -0.1811 0.6826 0.3667
-1.250 0.6553 0.00822 0.00206 -0.1812 0.6759 0.3885
-1.000 0.6841 0.00825 0.00208 -0.1813 0.6688 0.4043
-0.750 0.7128 0.00827 0.00210 -0.1814 0.6624 0.4209
-0.500 0.7416 0.00828 0.00214 -0.1815 0.6549 0.4401
0.000 0.7989 0.00832 0.00223 -0.1817 0.6402 0.4725
0.250 0.8270 0.00839 0.00228 -0.1817 0.6324 0.4823
0.750 0.8834 0.00852 0.00241 -0.1817 0.6157 0.5050
1.000 0.9115 0.00858 0.00249 -0.1817 0.6052 0.5202
1.250 0.9388 0.00868 0.00258 -0.1815 0.5914 0.5376
1.500 0.9657 0.00882 0.00268 -0.1812 0.5751 0.5543
1.750 0.9927 0.00895 0.00279 -0.1810 0.5608 0.5694
2.000 1.0197 0.00909 0.00292 -0.1808 0.5479 0.5834
2.250 1.0464 0.00925 0.00305 -0.1805 0.5342 0.5963
2.500 1.0729 0.00942 0.00319 -0.1802 0.5195 0.6086
2.750 1.0994 0.00960 0.00335 -0.1799 0.5046 0.6199
3.000 1.1255 0.00981 0.00352 -0.1795 0.4886 0.6305
3.250 1.1509 0.01006 0.00371 -0.1790 0.4706 0.6413
3.500 1.1764 0.01031 0.00393 -0.1786 0.4532 0.6519
3.750 1.2017 0.01058 0.00416 -0.1781 0.4369 0.6622
4.000 1.2269 0.01085 0.00439 -0.1776 0.4213 0.6726
4.250 1.2519 0.01113 0.00465 -0.1771 0.4056 0.6820
4.500 1.2766 0.01144 0.00491 -0.1765 0.3876 0.6918
4.750 1.3008 0.01177 0.00519 -0.1759 0.3666 0.7014
5.000 1.3245 0.01215 0.00549 -0.1752 0.3450 0.7110
5.250 1.3480 0.01253 0.00582 -0.1745 0.3239 0.7213
5.500 1.3707 0.01296 0.00618 -0.1736 0.2996 0.7314
5.750 1.3921 0.01349 0.00659 -0.1726 0.2720 0.7423
6.000 1.4130 0.01405 0.00706 -0.1715 0.2464 0.7556
6.250 1.4345 0.01454 0.00750 -0.1705 0.2267 0.7704
6.500 1.4556 0.01505 0.00796 -0.1694 0.2088 0.7868
6.750 1.4759 0.01557 0.00845 -0.1682 0.1911 0.8061
7.000 1.4955 0.01607 0.00896 -0.1668 0.1747 0.8295
7.250 1.5127 0.01654 0.00945 -0.1650 0.1590 0.8696
7.750 1.5425 0.01756 0.01042 -0.1604 0.1288 1.0000
8.000 1.5585 0.01824 0.01104 -0.1585 0.1138 1.0000
8.250 1.5731 0.01894 0.01168 -0.1564 0.1017 1.0000
8.750 1.6024 0.02031 0.01302 -0.1523 0.0860 1.0000
9.000 1.6157 0.02109 0.01380 -0.1502 0.0797 1.0000
9.250 1.6305 0.02178 0.01453 -0.1483 0.0751 1.0000
9.500 1.6433 0.02262 0.01537 -0.1462 0.0702 1.0000
9.750 1.6563 0.02346 0.01625 -0.1442 0.0663 1.0000
10.000 1.6695 0.02431 0.01714 -0.1423 0.0619 1.0000
10.250 1.6794 0.02542 0.01825 -0.1401 0.0566 1.0000
10.500 1.6914 0.02641 0.01928 -0.1383 0.0520 1.0000
10.750 1.7005 0.02765 0.02052 -0.1362 0.0475 1.0000
11.000 1.7113 0.02881 0.02172 -0.1345 0.0446 1.0000
11.250 1.7211 0.03008 0.02304 -0.1327 0.0421 1.0000
11.500 1.7292 0.03155 0.02454 -0.1309 0.0395 1.0000
11.750 1.7385 0.03296 0.02602 -0.1294 0.0378 1.0000
12.000 1.7471 0.03447 0.02760 -0.1278 0.0362 1.0000
12.250 1.7544 0.03615 0.02934 -0.1263 0.0345 1.0000
12.500 1.7603 0.03804 0.03128 -0.1249 0.0329 1.0000
12.750 1.7670 0.03989 0.03321 -0.1236 0.0316 1.0000
13.000 1.7740 0.04176 0.03518 -0.1224 0.0305 1.0000
13.250 1.7796 0.04383 0.03733 -0.1213 0.0292 1.0000
13.500 1.7837 0.04612 0.03970 -0.1203 0.0278 1.0000
13.750 1.7859 0.04871 0.04235 -0.1193 0.0265 1.0000
14.000 1.7917 0.05094 0.04469 -0.1185 0.0254 1.0000
14.250 1.7958 0.05345 0.04729 -0.1179 0.0239 1.0000
14.500 1.7979 0.05626 0.05018 -0.1173 0.0225 1.0000
14.750 1.7995 0.05922 0.05323 -0.1169 0.0212 1.0000
15.000 1.8016 0.06219 0.05630 -0.1166 0.0196 1.0000
15.250 1.8018 0.06549 0.05968 -0.1164 0.0182 1.0000
15.500 1.8011 0.06902 0.06330 -0.1164 0.0169 1.0000
15.750 1.7997 0.07275 0.06712 -0.1166 0.0156 1.0000
16.000 1.7966 0.07680 0.07125 -0.1170 0.0145 1.0000
16.250 1.7928 0.08108 0.07563 -0.1175 0.0135 1.0000
16.500 1.7890 0.08545 0.08012 -0.1183 0.0128 1.0000
16.750 1.7838 0.09015 0.08492 -0.1192 0.0120 1.0000
17.000 1.7771 0.09521 0.09009 -0.1205 0.0114 1.0000
17.250 1.7700 0.10040 0.09539 -0.1219 0.0109 1.0000
17.500 1.7639 0.10553 0.10066 -0.1235 0.0105 1.0000
17.750 1.7569 0.11088 0.10615 -0.1253 0.0100 1.0000
18.000 1.7500 0.11629 0.11169 -0.1274 0.0098 1.0000
18.250 1.7416 0.12204 0.11757 -0.1297 0.0095 1.0000
18.500 1.7328 0.12790 0.12355 -0.1322 0.0092 1.0000
18.750 1.7237 0.13389 0.12966 -0.1350 0.0089 1.0000
19.000 1.7140 0.14005 0.13594 -0.1381 0.0087 1.0000
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