FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 200,000 Max Cl/Cd: 89.96 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63120-il-200000-n5.txt Download as CSV file: xf-fx63120-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2526 0.08725 0.08365 -0.0660 0.9797 0.0231
-9.000 -0.2478 0.08116 0.07757 -0.0713 0.9717 0.0232
-8.750 -0.2500 0.07363 0.07006 -0.0777 0.9601 0.0233
-8.500 -0.2588 0.06456 0.06101 -0.0856 0.9453 0.0234
-8.250 -0.2787 0.03563 0.03103 -0.1298 0.9204 0.0238
-8.000 -0.2466 0.03415 0.02949 -0.1335 0.9154 0.0245
-7.750 -0.2092 0.03177 0.02687 -0.1391 0.9119 0.0258
-7.500 -0.1725 0.02736 0.02181 -0.1461 0.9065 0.0271
-7.250 -0.1336 0.02408 0.01778 -0.1513 0.9012 0.0288
-7.000 -0.0965 0.02265 0.01627 -0.1544 0.8970 0.0300
-6.750 -0.0587 0.02136 0.01478 -0.1574 0.8926 0.0314
-6.500 -0.0254 0.02005 0.01321 -0.1592 0.8858 0.0325
-6.250 0.0117 0.01896 0.01181 -0.1616 0.8805 0.0343
-6.000 0.0460 0.01784 0.01056 -0.1634 0.8747 0.0356
-5.750 0.0773 0.01705 0.00972 -0.1644 0.8675 0.0367
-5.500 0.1116 0.01634 0.00891 -0.1659 0.8619 0.0379
-5.250 0.1416 0.01582 0.00830 -0.1666 0.8546 0.0398
-5.000 0.1734 0.01529 0.00766 -0.1675 0.8478 0.0413
-4.750 0.2055 0.01469 0.00700 -0.1686 0.8416 0.0426
-4.500 0.2358 0.01421 0.00650 -0.1693 0.8343 0.0442
-4.250 0.2684 0.01384 0.00607 -0.1704 0.8282 0.0464
-4.000 0.2983 0.01355 0.00572 -0.1710 0.8209 0.0493
-3.750 0.3301 0.01321 0.00532 -0.1719 0.8141 0.0522
-3.500 0.3614 0.01293 0.00499 -0.1727 0.8070 0.0566
-3.250 0.3921 0.01268 0.00467 -0.1733 0.7984 0.0634
-3.000 0.4234 0.01239 0.00439 -0.1741 0.7902 0.0815
-2.750 0.4559 0.01193 0.00413 -0.1754 0.7820 0.1461
-2.500 0.4898 0.01135 0.00399 -0.1773 0.7752 0.2864
-2.250 0.5196 0.01126 0.00405 -0.1778 0.7676 0.3709
-2.000 0.5496 0.01126 0.00402 -0.1781 0.7614 0.4103
-1.750 0.5781 0.01124 0.00405 -0.1782 0.7537 0.4409
-1.500 0.6074 0.01123 0.00408 -0.1783 0.7471 0.4704
-1.250 0.6357 0.01126 0.00416 -0.1783 0.7398 0.4959
-1.000 0.6643 0.01130 0.00418 -0.1782 0.7328 0.5129
-0.750 0.6928 0.01134 0.00421 -0.1782 0.7259 0.5274
-0.500 0.7210 0.01139 0.00425 -0.1782 0.7184 0.5405
-0.250 0.7495 0.01145 0.00428 -0.1781 0.7118 0.5516
0.000 0.7773 0.01150 0.00434 -0.1780 0.7038 0.5630
0.500 0.8332 0.01164 0.00447 -0.1778 0.6887 0.5887
0.750 0.8613 0.01172 0.00453 -0.1777 0.6814 0.6021
1.000 0.8886 0.01180 0.00465 -0.1774 0.6728 0.6153
1.250 0.9164 0.01190 0.00472 -0.1773 0.6650 0.6285
1.500 0.9436 0.01200 0.00485 -0.1770 0.6558 0.6419
1.750 0.9709 0.01210 0.00495 -0.1768 0.6473 0.6543
2.000 0.9975 0.01221 0.00509 -0.1764 0.6370 0.6670
2.250 1.0239 0.01232 0.00521 -0.1760 0.6251 0.6800
2.500 1.0499 0.01246 0.00532 -0.1755 0.6115 0.6930
2.750 1.0757 0.01260 0.00545 -0.1749 0.5979 0.7052
3.000 1.1015 0.01274 0.00562 -0.1744 0.5853 0.7169
3.250 1.1274 0.01290 0.00579 -0.1739 0.5727 0.7289
3.500 1.1530 0.01307 0.00598 -0.1734 0.5598 0.7413
3.750 1.1782 0.01325 0.00618 -0.1728 0.5465 0.7537
4.000 1.2029 0.01345 0.00639 -0.1721 0.5327 0.7667
4.250 1.2270 0.01367 0.00661 -0.1713 0.5185 0.7808
4.500 1.2504 0.01390 0.00685 -0.1703 0.5029 0.7959
4.750 1.2728 0.01416 0.00710 -0.1692 0.4853 0.8127
5.000 1.2938 0.01444 0.00737 -0.1678 0.4662 0.8324
5.250 1.3125 0.01472 0.00766 -0.1659 0.4475 0.8595
5.500 1.3253 0.01486 0.00783 -0.1628 0.4305 0.9983
5.750 1.3484 0.01534 0.00823 -0.1621 0.4106 1.0000
6.000 1.3708 0.01582 0.00864 -0.1612 0.3925 1.0000
6.250 1.3930 0.01630 0.00909 -0.1604 0.3750 1.0000
6.500 1.4148 0.01678 0.00955 -0.1594 0.3571 1.0000
6.750 1.4348 0.01735 0.01005 -0.1582 0.3340 1.0000
7.000 1.4521 0.01804 0.01063 -0.1566 0.3066 1.0000
7.250 1.4674 0.01885 0.01130 -0.1547 0.2780 1.0000
7.500 1.4820 0.01968 0.01201 -0.1527 0.2525 1.0000
7.750 1.4953 0.02051 0.01275 -0.1505 0.2320 1.0000
8.000 1.5084 0.02132 0.01352 -0.1483 0.2147 1.0000
8.250 1.5210 0.02218 0.01435 -0.1460 0.1987 1.0000
8.500 1.5328 0.02310 0.01524 -0.1438 0.1827 1.0000
8.750 1.5437 0.02410 0.01621 -0.1414 0.1664 1.0000
9.000 1.5535 0.02519 0.01726 -0.1391 0.1502 1.0000
9.250 1.5625 0.02638 0.01841 -0.1368 0.1349 1.0000
9.500 1.5710 0.02765 0.01967 -0.1345 0.1217 1.0000
9.750 1.5793 0.02899 0.02100 -0.1323 0.1110 1.0000
10.000 1.5867 0.03044 0.02246 -0.1302 0.1025 1.0000
10.250 1.5944 0.03192 0.02398 -0.1283 0.0953 1.0000
10.500 1.6011 0.03355 0.02565 -0.1264 0.0896 1.0000
10.750 1.6084 0.03518 0.02737 -0.1246 0.0842 1.0000
11.000 1.6122 0.03719 0.02940 -0.1228 0.0795 1.0000
11.250 1.6199 0.03890 0.03123 -0.1214 0.0754 1.0000
11.500 1.6253 0.04089 0.03330 -0.1199 0.0716 1.0000
11.750 1.6275 0.04325 0.03571 -0.1185 0.0683 1.0000
12.000 1.6331 0.04535 0.03793 -0.1173 0.0650 1.0000
12.250 1.6387 0.04751 0.04020 -0.1163 0.0614 1.0000
12.500 1.6410 0.05007 0.04282 -0.1153 0.0582 1.0000
12.750 1.6435 0.05269 0.04553 -0.1144 0.0555 1.0000
13.000 1.6485 0.05509 0.04806 -0.1137 0.0527 1.0000
13.250 1.6513 0.05782 0.05089 -0.1132 0.0501 1.0000
13.500 1.6515 0.06095 0.05409 -0.1127 0.0481 1.0000
13.750 1.6525 0.06406 0.05731 -0.1124 0.0462 1.0000
14.000 1.6551 0.06705 0.06046 -0.1122 0.0443 1.0000
14.250 1.6563 0.07029 0.06383 -0.1122 0.0422 1.0000
14.500 1.6553 0.07393 0.06756 -0.1123 0.0406 1.0000
14.750 1.6516 0.07806 0.07177 -0.1127 0.0392 1.0000
15.000 1.6524 0.08160 0.07547 -0.1131 0.0376 1.0000
15.250 1.6518 0.08544 0.07946 -0.1136 0.0360 1.0000
15.500 1.6498 0.08959 0.08373 -0.1144 0.0345 1.0000
15.750 1.6453 0.09421 0.08845 -0.1155 0.0332 1.0000
16.000 1.6398 0.09908 0.09342 -0.1169 0.0320 1.0000
16.250 1.6385 0.10333 0.09786 -0.1180 0.0306 1.0000
16.500 1.6354 0.10794 0.10263 -0.1195 0.0292 1.0000
16.750 1.6310 0.11287 0.10770 -0.1213 0.0280 1.0000
17.000 1.6240 0.11832 0.11323 -0.1235 0.0269 1.0000
17.250 1.6192 0.12340 0.11846 -0.1256 0.0259 1.0000
17.500 1.6158 0.12830 0.12354 -0.1278 0.0246 1.0000
17.750 1.6111 0.13352 0.12890 -0.1303 0.0235 1.0000
18.000 1.6056 0.13891 0.13442 -0.1330 0.0227 1.0000
18.250 1.5988 0.14467 0.14027 -0.1362 0.0220 1.0000
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