FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 500,000 Max Cl/Cd: 122.8 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k153-il-500000-n5.txt Download as CSV file: xf-fx62k153-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 62-K-153/20 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 -0.4431 0.04766 0.04423 -0.1316 0.8453 0.0040
-12.000 -0.4701 0.04072 0.03698 -0.1359 0.8398 0.0039
-11.750 -0.4871 0.03570 0.03162 -0.1380 0.8350 0.0039
-11.250 -0.4932 0.02909 0.02441 -0.1395 0.8278 0.0040
-11.000 -0.4870 0.02684 0.02191 -0.1397 0.8246 0.0040
-10.750 -0.4771 0.02506 0.01987 -0.1398 0.8216 0.0041
-10.500 -0.4624 0.02332 0.01791 -0.1405 0.8189 0.0042
-10.000 -0.4211 0.02114 0.01546 -0.1419 0.8142 0.0046
-9.750 -0.3985 0.02029 0.01450 -0.1424 0.8121 0.0048
-9.500 -0.3756 0.01947 0.01355 -0.1428 0.8100 0.0050
-9.250 -0.3522 0.01867 0.01263 -0.1432 0.8080 0.0054
-9.000 -0.3285 0.01787 0.01168 -0.1435 0.8060 0.0058
-8.750 -0.3042 0.01713 0.01081 -0.1438 0.8040 0.0062
-8.500 -0.2783 0.01665 0.01027 -0.1443 0.8022 0.0067
-8.250 -0.2522 0.01620 0.00977 -0.1448 0.8005 0.0074
-8.000 -0.2263 0.01569 0.00918 -0.1452 0.7988 0.0083
-7.750 -0.2002 0.01518 0.00861 -0.1457 0.7969 0.0090
-7.500 -0.1733 0.01481 0.00820 -0.1462 0.7950 0.0098
-7.250 -0.1461 0.01447 0.00781 -0.1467 0.7930 0.0109
-7.000 -0.1184 0.01421 0.00748 -0.1472 0.7913 0.0119
-6.750 -0.0908 0.01382 0.00708 -0.1479 0.7897 0.0135
-6.500 -0.0624 0.01360 0.00682 -0.1486 0.7882 0.0151
-6.250 -0.0339 0.01328 0.00643 -0.1493 0.7865 0.0164
-6.000 -0.0058 0.01280 0.00594 -0.1501 0.7848 0.0178
-5.750 0.0228 0.01245 0.00557 -0.1509 0.7831 0.0189
-5.500 0.0519 0.01214 0.00522 -0.1517 0.7812 0.0202
-5.250 0.0813 0.01187 0.00489 -0.1525 0.7793 0.0217
-5.000 0.1111 0.01153 0.00456 -0.1535 0.7776 0.0252
-4.750 0.1411 0.01130 0.00429 -0.1544 0.7759 0.0289
-4.500 0.1716 0.01105 0.00404 -0.1554 0.7743 0.0375
-4.250 0.2025 0.01081 0.00382 -0.1566 0.7727 0.0521
-4.000 0.2333 0.01056 0.00363 -0.1578 0.7711 0.0758
-3.750 0.2649 0.01017 0.00344 -0.1593 0.7692 0.1269
-3.500 0.3014 0.00936 0.00312 -0.1626 0.7673 0.2725
-3.250 0.3460 0.00824 0.00284 -0.1681 0.7655 0.5229
-3.000 0.3774 0.00818 0.00287 -0.1691 0.7635 0.5711
-2.750 0.4077 0.00820 0.00291 -0.1697 0.7616 0.6002
-2.500 0.4375 0.00830 0.00303 -0.1702 0.7597 0.6270
-2.250 0.4675 0.00844 0.00312 -0.1707 0.7580 0.6438
-2.000 0.4965 0.00848 0.00315 -0.1711 0.7560 0.6474
-1.750 0.5254 0.00852 0.00317 -0.1714 0.7538 0.6507
-1.500 0.5547 0.00855 0.00318 -0.1719 0.7514 0.6545
-1.250 0.5846 0.00857 0.00316 -0.1726 0.7490 0.6581
-1.000 0.6139 0.00859 0.00315 -0.1731 0.7465 0.6607
-0.750 0.6432 0.00862 0.00316 -0.1735 0.7442 0.6629
-0.500 0.6723 0.00866 0.00319 -0.1739 0.7417 0.6654
-0.250 0.7008 0.00869 0.00323 -0.1743 0.7383 0.6682
0.000 0.7297 0.00870 0.00323 -0.1747 0.7346 0.6712
0.250 0.7592 0.00872 0.00321 -0.1753 0.7310 0.6739
0.500 0.7881 0.00875 0.00322 -0.1756 0.7279 0.6758
0.750 0.8162 0.00878 0.00330 -0.1759 0.7246 0.6776
1.000 0.8446 0.00882 0.00337 -0.1762 0.7212 0.6796
1.250 0.8732 0.00885 0.00342 -0.1766 0.7179 0.6818
1.500 0.9022 0.00889 0.00345 -0.1770 0.7150 0.6841
1.750 0.9309 0.00894 0.00353 -0.1774 0.7117 0.6863
2.000 0.9594 0.00899 0.00360 -0.1778 0.7077 0.6885
2.250 0.9875 0.00902 0.00366 -0.1780 0.7029 0.6903
2.500 1.0147 0.00905 0.00372 -0.1781 0.6964 0.6920
2.750 1.0413 0.00908 0.00377 -0.1780 0.6871 0.6937
3.000 1.0680 0.00913 0.00385 -0.1779 0.6781 0.6955
3.250 1.0949 0.00921 0.00393 -0.1779 0.6705 0.6976
3.500 1.1213 0.00928 0.00403 -0.1778 0.6600 0.6997
3.750 1.1472 0.00939 0.00413 -0.1776 0.6476 0.7018
4.000 1.1715 0.00954 0.00424 -0.1770 0.6303 0.7038
4.250 1.1940 0.00975 0.00440 -0.1761 0.6093 0.7055
4.500 1.2135 0.01008 0.00463 -0.1746 0.5817 0.7071
4.750 1.2288 0.01058 0.00496 -0.1723 0.5434 0.7088
5.000 1.2430 0.01114 0.00537 -0.1699 0.5072 0.7105
5.250 1.2575 0.01169 0.00579 -0.1676 0.4757 0.7124
5.500 1.2716 0.01221 0.00622 -0.1652 0.4492 0.7145
5.750 1.2828 0.01276 0.00667 -0.1623 0.4230 0.7167
6.000 1.2933 0.01345 0.00724 -0.1593 0.3930 0.7187
6.250 1.2995 0.01439 0.00800 -0.1558 0.3500 0.7203
6.500 1.2996 0.01566 0.00899 -0.1514 0.2981 0.7219
6.750 1.3033 0.01685 0.00999 -0.1478 0.2579 0.7235
7.000 1.3103 0.01796 0.01095 -0.1450 0.2250 0.7253
7.250 1.3168 0.01916 0.01200 -0.1421 0.1910 0.7273
7.500 1.3225 0.02047 0.01313 -0.1394 0.1560 0.7293
7.750 1.3295 0.02176 0.01428 -0.1369 0.1284 0.7312
8.000 1.3375 0.02304 0.01545 -0.1346 0.1053 0.7329
8.250 1.3479 0.02417 0.01652 -0.1328 0.0888 0.7345
8.500 1.3596 0.02523 0.01756 -0.1311 0.0771 0.7361
8.750 1.3711 0.02631 0.01863 -0.1294 0.0667 0.7377
9.000 1.3825 0.02742 0.01973 -0.1277 0.0572 0.7395
9.250 1.3931 0.02859 0.02089 -0.1261 0.0477 0.7413
9.500 1.4039 0.02978 0.02207 -0.1245 0.0401 0.7431
9.750 1.4140 0.03103 0.02333 -0.1228 0.0333 0.7448
10.000 1.4254 0.03219 0.02451 -0.1214 0.0288 0.7466
10.250 1.4354 0.03347 0.02580 -0.1198 0.0247 0.7484
10.500 1.4462 0.03470 0.02708 -0.1183 0.0217 0.7501
10.750 1.4551 0.03609 0.02850 -0.1167 0.0186 0.7517
11.000 1.4657 0.03736 0.02984 -0.1153 0.0161 0.7535
11.250 1.4739 0.03885 0.03136 -0.1138 0.0137 0.7552
11.500 1.4834 0.04026 0.03285 -0.1124 0.0112 0.7569
11.750 1.4890 0.04205 0.03465 -0.1107 0.0068 0.7586
12.000 1.4938 0.04393 0.03656 -0.1091 0.0044 0.7604
12.250 1.4996 0.04576 0.03844 -0.1075 0.0037 0.7622
12.500 1.5052 0.04765 0.04041 -0.1061 0.0032 0.7640
12.750 1.5113 0.04952 0.04240 -0.1047 0.0028 0.7658
13.000 1.5176 0.05142 0.04439 -0.1035 0.0027 0.7676
13.250 1.5225 0.05349 0.04657 -0.1022 0.0025 0.7694
13.500 1.5268 0.05565 0.04884 -0.1010 0.0024 0.7713
13.750 1.5297 0.05800 0.05130 -0.0998 0.0023 0.7732
14.000 1.5324 0.06042 0.05386 -0.0987 0.0022 0.7750
14.250 1.5354 0.06287 0.05641 -0.0977 0.0021 0.7769
14.500 1.5382 0.06538 0.05904 -0.0969 0.0021 0.7787
14.750 1.5403 0.06802 0.06181 -0.0961 0.0020 0.7805
15.000 1.5414 0.07081 0.06473 -0.0953 0.0020 0.7825
15.250 1.5417 0.07375 0.06780 -0.0947 0.0020 0.7847
15.500 1.5415 0.07684 0.07102 -0.0942 0.0019 0.7870
15.750 1.5402 0.08011 0.07441 -0.0938 0.0019 0.7893
16.000 1.5375 0.08363 0.07808 -0.0936 0.0018 0.7916
16.250 1.5347 0.08724 0.08182 -0.0935 0.0018 0.7936
16.500 1.5299 0.09117 0.08590 -0.0936 0.0017 0.7956
16.750 1.5258 0.09509 0.08995 -0.0939 0.0017 0.7979
17.000 1.5205 0.09928 0.09429 -0.0944 0.0017 0.8003
17.250 1.5137 0.10376 0.09891 -0.0951 0.0016 0.8027
17.500 1.5072 0.10830 0.10361 -0.0961 0.0016 0.8052
18.000 1.4908 0.11813 0.11373 -0.0988 0.0016 0.8102
18.250 1.4825 0.12324 0.11898 -0.1005 0.0016 0.8131
18.500 1.4723 0.12880 0.12470 -0.1026 0.0015 0.8162
18.750 1.4634 0.13424 0.13029 -0.1050 0.0015 0.8197
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