FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.28 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k153-il-1000000-n5.txt Download as CSV file: xf-fx62k153-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5727 0.05632 0.05344 -0.1214 0.8353 0.0024
-14.000 -0.6045 0.04702 0.04388 -0.1286 0.8305 0.0024
-13.750 -0.6223 0.04135 0.03801 -0.1323 0.8263 0.0024
-13.500 -0.6317 0.03728 0.03374 -0.1344 0.8220 0.0024
-13.250 -0.6363 0.03401 0.03027 -0.1358 0.8179 0.0024
-13.000 -0.6364 0.03131 0.02738 -0.1367 0.8144 0.0024
-12.750 -0.6329 0.02899 0.02489 -0.1373 0.8112 0.0024
-12.500 -0.6258 0.02704 0.02278 -0.1377 0.8082 0.0024
-12.250 -0.6162 0.02532 0.02090 -0.1380 0.8054 0.0024
-12.000 -0.6042 0.02381 0.01923 -0.1383 0.8029 0.0024
-11.750 -0.5914 0.02248 0.01777 -0.1383 0.8007 0.0024
-11.500 -0.5749 0.02129 0.01646 -0.1387 0.7986 0.0024
-11.250 -0.5552 0.02018 0.01522 -0.1395 0.7964 0.0025
-11.000 -0.5337 0.01919 0.01411 -0.1403 0.7941 0.0025
-10.750 -0.5109 0.01830 0.01310 -0.1411 0.7920 0.0025
-10.500 -0.4881 0.01736 0.01203 -0.1418 0.7902 0.0025
-10.250 -0.4648 0.01651 0.01105 -0.1424 0.7884 0.0026
-10.000 -0.4404 0.01580 0.01024 -0.1429 0.7867 0.0027
-9.750 -0.4151 0.01516 0.00953 -0.1434 0.7853 0.0029
-9.500 -0.3893 0.01460 0.00892 -0.1439 0.7837 0.0030
-9.250 -0.3630 0.01409 0.00835 -0.1445 0.7820 0.0032
-9.000 -0.3364 0.01362 0.00783 -0.1451 0.7802 0.0034
-8.750 -0.3093 0.01319 0.00734 -0.1457 0.7786 0.0037
-8.500 -0.2819 0.01279 0.00689 -0.1463 0.7771 0.0040
-8.250 -0.2543 0.01241 0.00649 -0.1470 0.7755 0.0047
-8.000 -0.2262 0.01209 0.00614 -0.1476 0.7739 0.0057
-7.500 -0.1693 0.01154 0.00555 -0.1490 0.7710 0.0075
-7.250 -0.1405 0.01129 0.00528 -0.1497 0.7696 0.0083
-7.000 -0.1115 0.01104 0.00500 -0.1505 0.7681 0.0089
-6.750 -0.0825 0.01077 0.00472 -0.1512 0.7664 0.0097
-6.500 -0.0532 0.01054 0.00448 -0.1520 0.7649 0.0105
-6.250 -0.0239 0.01034 0.00425 -0.1528 0.7633 0.0113
-6.000 0.0056 0.01015 0.00404 -0.1535 0.7617 0.0120
-5.750 0.0354 0.00990 0.00377 -0.1544 0.7601 0.0133
-5.500 0.0652 0.00972 0.00357 -0.1552 0.7586 0.0148
-5.250 0.0951 0.00956 0.00338 -0.1561 0.7571 0.0160
-5.000 0.1254 0.00934 0.00317 -0.1570 0.7556 0.0184
-4.750 0.1557 0.00915 0.00299 -0.1579 0.7541 0.0208
-4.500 0.1862 0.00896 0.00282 -0.1589 0.7524 0.0263
-4.250 0.2167 0.00877 0.00266 -0.1598 0.7506 0.0356
-4.000 0.2474 0.00859 0.00252 -0.1608 0.7488 0.0484
-3.750 0.2782 0.00842 0.00239 -0.1618 0.7469 0.0648
-3.500 0.3095 0.00821 0.00225 -0.1630 0.7452 0.0927
-3.250 0.3427 0.00787 0.00210 -0.1649 0.7434 0.1585
-3.000 0.3828 0.00703 0.00183 -0.1689 0.7418 0.3408
-2.750 0.4231 0.00636 0.00165 -0.1727 0.7402 0.5026
-2.500 0.4557 0.00622 0.00163 -0.1741 0.7383 0.5503
-2.250 0.4871 0.00616 0.00164 -0.1751 0.7363 0.5857
-2.000 0.5177 0.00617 0.00170 -0.1758 0.7340 0.6172
-1.750 0.5474 0.00620 0.00171 -0.1764 0.7314 0.6267
-1.500 0.5769 0.00623 0.00170 -0.1769 0.7286 0.6306
-1.250 0.6065 0.00624 0.00171 -0.1775 0.7258 0.6339
-1.000 0.6361 0.00625 0.00173 -0.1780 0.7225 0.6375
-0.750 0.6655 0.00627 0.00172 -0.1785 0.7190 0.6410
-0.500 0.6947 0.00630 0.00172 -0.1790 0.7157 0.6439
-0.250 0.7240 0.00633 0.00174 -0.1794 0.7127 0.6462
0.000 0.7534 0.00635 0.00178 -0.1800 0.7097 0.6486
0.250 0.7827 0.00638 0.00182 -0.1805 0.7065 0.6512
0.500 0.8118 0.00641 0.00185 -0.1809 0.7035 0.6539
0.750 0.8408 0.00646 0.00188 -0.1813 0.7004 0.6565
1.000 0.8699 0.00650 0.00192 -0.1818 0.6968 0.6587
1.250 0.8988 0.00653 0.00197 -0.1822 0.6920 0.6607
1.500 0.9270 0.00658 0.00202 -0.1825 0.6863 0.6625
1.750 0.9553 0.00663 0.00208 -0.1828 0.6785 0.6645
2.000 0.9826 0.00671 0.00213 -0.1829 0.6684 0.6666
2.250 1.0097 0.00680 0.00220 -0.1829 0.6573 0.6686
2.500 1.0369 0.00690 0.00228 -0.1830 0.6457 0.6705
2.750 1.0632 0.00705 0.00238 -0.1828 0.6314 0.6725
3.000 1.0892 0.00720 0.00249 -0.1827 0.6173 0.6743
3.250 1.1131 0.00744 0.00266 -0.1821 0.5958 0.6760
3.500 1.1355 0.00776 0.00288 -0.1812 0.5690 0.6777
3.750 1.1575 0.00810 0.00312 -0.1803 0.5417 0.6795
4.000 1.1745 0.00869 0.00349 -0.1784 0.4960 0.6814
4.250 1.1903 0.00933 0.00390 -0.1763 0.4489 0.6833
4.500 1.2090 0.00982 0.00424 -0.1748 0.4164 0.6852
4.750 1.2282 0.01026 0.00457 -0.1734 0.3908 0.6870
5.000 1.2472 0.01070 0.00492 -0.1720 0.3654 0.6887
5.250 1.2610 0.01132 0.00536 -0.1696 0.3263 0.6903
5.500 1.2681 0.01206 0.00591 -0.1659 0.2859 0.6919
5.750 1.2763 0.01291 0.00655 -0.1626 0.2440 0.6935
6.000 1.2844 0.01379 0.00724 -0.1594 0.2045 0.6953
6.250 1.2918 0.01474 0.00799 -0.1561 0.1640 0.6971
6.500 1.2991 0.01574 0.00881 -0.1530 0.1305 0.6990
6.750 1.3094 0.01664 0.00958 -0.1505 0.1057 0.7007
7.000 1.3231 0.01738 0.01027 -0.1485 0.0911 0.7023
7.250 1.3366 0.01816 0.01099 -0.1467 0.0770 0.7037
7.500 1.3499 0.01899 0.01177 -0.1449 0.0641 0.7051
7.750 1.3633 0.01983 0.01258 -0.1431 0.0535 0.7068
8.000 1.3779 0.02061 0.01336 -0.1416 0.0463 0.7084
8.250 1.3917 0.02147 0.01421 -0.1400 0.0383 0.7101
8.500 1.4046 0.02240 0.01512 -0.1383 0.0308 0.7117
8.750 1.4170 0.02338 0.01607 -0.1366 0.0245 0.7132
9.000 1.4301 0.02433 0.01703 -0.1351 0.0205 0.7148
9.250 1.4436 0.02527 0.01798 -0.1336 0.0172 0.7164
9.500 1.4561 0.02627 0.01900 -0.1321 0.0146 0.7181
10.000 1.4787 0.02850 0.02125 -0.1288 0.0075 0.7210
10.250 1.4850 0.03000 0.02275 -0.1266 0.0030 0.7224
10.500 1.4953 0.03121 0.02401 -0.1250 0.0024 0.7239
10.750 1.5062 0.03240 0.02526 -0.1234 0.0021 0.7254
11.000 1.5176 0.03356 0.02648 -0.1220 0.0020 0.7270
11.250 1.5283 0.03480 0.02779 -0.1205 0.0019 0.7288
11.500 1.5387 0.03607 0.02912 -0.1191 0.0018 0.7305
11.750 1.5477 0.03746 0.03058 -0.1175 0.0017 0.7320
12.000 1.5566 0.03889 0.03207 -0.1160 0.0016 0.7334
12.250 1.5653 0.04037 0.03362 -0.1145 0.0015 0.7347
12.500 1.5729 0.04197 0.03531 -0.1130 0.0014 0.7361
12.750 1.5791 0.04373 0.03715 -0.1115 0.0013 0.7375
13.000 1.5860 0.04543 0.03893 -0.1101 0.0013 0.7391
13.250 1.5913 0.04732 0.04091 -0.1086 0.0012 0.7408
13.500 1.5984 0.04909 0.04277 -0.1073 0.0012 0.7425
13.750 1.6046 0.05098 0.04474 -0.1061 0.0012 0.7443
14.000 1.6109 0.05288 0.04672 -0.1049 0.0012 0.7459
14.250 1.6156 0.05496 0.04888 -0.1038 0.0011 0.7474
14.500 1.6197 0.05714 0.05114 -0.1026 0.0011 0.7488
14.750 1.6236 0.05941 0.05351 -0.1016 0.0011 0.7502
15.000 1.6269 0.06177 0.05597 -0.1006 0.0010 0.7518
15.250 1.6291 0.06431 0.05860 -0.0997 0.0010 0.7533
15.500 1.6307 0.06696 0.06135 -0.0988 0.0010 0.7550
15.750 1.6312 0.06978 0.06427 -0.0981 0.0010 0.7567
16.000 1.6307 0.07275 0.06735 -0.0974 0.0009 0.7585
16.250 1.6304 0.07578 0.07048 -0.0968 0.0009 0.7604
16.500 1.6274 0.07920 0.07401 -0.0963 0.0009 0.7620
17.000 1.6226 0.08610 0.08114 -0.0959 0.0009 0.7654
17.250 1.6179 0.08993 0.08509 -0.0959 0.0008 0.7671
17.500 1.6130 0.09385 0.08912 -0.0961 0.0008 0.7688
17.750 1.6072 0.09799 0.09338 -0.0965 0.0008 0.7706
18.000 1.6002 0.10238 0.09789 -0.0971 0.0008 0.7724
18.250 1.5933 0.10684 0.10247 -0.0979 0.0008 0.7742
18.500 1.5844 0.11169 0.10745 -0.0990 0.0008 0.7759
18.750 1.5750 0.11668 0.11255 -0.1003 0.0008 0.7776
19.000 1.5665 0.12162 0.11761 -0.1018 0.0007 0.7793
19.250 1.5560 0.12701 0.12314 -0.1037 0.0007 0.7812
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