FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 100,000 Max Cl/Cd: 67.12 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63120-il-100000-n5.txt Download as CSV file: xf-fx63120-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3014 0.12008 0.11511 -0.0442 1.0000 0.0609
-10.000 -0.3097 0.11797 0.11308 -0.0442 1.0000 0.0612
-9.750 -0.3187 0.11588 0.11109 -0.0434 1.0000 0.0613
-9.250 -0.3090 0.10433 0.09953 -0.0453 0.9967 0.0414
-9.000 -0.2926 0.10027 0.09546 -0.0485 0.9924 0.0406
-8.750 -0.2817 0.09505 0.09024 -0.0542 0.9865 0.0410
-8.500 -0.2719 0.09013 0.08533 -0.0591 0.9793 0.0410
-8.250 -0.2621 0.08545 0.08066 -0.0636 0.9716 0.0408
-8.000 -0.2519 0.08077 0.07599 -0.0683 0.9639 0.0403
-7.750 -0.2467 0.07573 0.07096 -0.0730 0.9538 0.0399
-7.250 -0.2359 0.05882 0.05398 -0.0942 0.9298 0.0388
-7.000 -0.2177 0.04641 0.04098 -0.1154 0.9182 0.0394
-6.750 -0.1803 0.03861 0.03230 -0.1282 0.9131 0.0410
-6.500 -0.1358 0.03345 0.02623 -0.1366 0.9107 0.0419
-6.250 -0.1082 0.03158 0.02428 -0.1384 0.9038 0.0436
-6.000 -0.0719 0.02985 0.02234 -0.1414 0.8997 0.0459
-5.750 -0.0303 0.02754 0.01957 -0.1454 0.8970 0.0474
-5.500 0.0119 0.02566 0.01726 -0.1489 0.8946 0.0495
-5.250 0.0424 0.02441 0.01579 -0.1500 0.8881 0.0518
-5.000 0.0769 0.02326 0.01457 -0.1516 0.8833 0.0536
-4.750 0.1143 0.02219 0.01338 -0.1536 0.8799 0.0557
-4.500 0.1515 0.02131 0.01238 -0.1555 0.8763 0.0589
-4.250 0.1799 0.02076 0.01173 -0.1557 0.8688 0.0619
-4.000 0.2158 0.01991 0.01092 -0.1575 0.8644 0.0652
-3.750 0.2552 0.01922 0.01018 -0.1598 0.8610 0.0697
-3.500 0.2847 0.01882 0.00972 -0.1604 0.8532 0.0761
-3.250 0.3221 0.01824 0.00909 -0.1625 0.8480 0.0878
-3.000 0.3646 0.01742 0.00837 -0.1658 0.8441 0.1185
-2.750 0.3992 0.01645 0.00817 -0.1684 0.8363 0.2849
-2.500 0.4347 0.01627 0.00813 -0.1698 0.8301 0.4015
-2.250 0.4656 0.01624 0.00819 -0.1702 0.8226 0.4603
-2.000 0.4947 0.01631 0.00835 -0.1700 0.8148 0.5062
-1.750 0.5249 0.01640 0.00842 -0.1699 0.8081 0.5384
-1.500 0.5526 0.01649 0.00847 -0.1697 0.7999 0.5579
-1.250 0.5851 0.01644 0.00834 -0.1702 0.7943 0.5714
-1.000 0.6103 0.01655 0.00843 -0.1696 0.7855 0.5840
-0.750 0.6418 0.01652 0.00833 -0.1700 0.7793 0.5971
-0.500 0.6692 0.01660 0.00837 -0.1698 0.7710 0.6095
-0.250 0.6987 0.01659 0.00833 -0.1699 0.7642 0.6205
0.000 0.7263 0.01666 0.00838 -0.1697 0.7564 0.6321
0.250 0.7552 0.01669 0.00839 -0.1697 0.7490 0.6454
0.500 0.7835 0.01676 0.00844 -0.1696 0.7414 0.6594
0.750 0.8108 0.01682 0.00850 -0.1693 0.7334 0.6723
1.000 0.8384 0.01689 0.00857 -0.1690 0.7258 0.6859
1.250 0.8651 0.01697 0.00867 -0.1686 0.7173 0.7004
1.500 0.8923 0.01704 0.00875 -0.1682 0.7093 0.7155
1.750 0.9188 0.01713 0.00886 -0.1678 0.7006 0.7306
2.000 0.9450 0.01722 0.00898 -0.1673 0.6918 0.7456
2.250 0.9718 0.01728 0.00905 -0.1668 0.6831 0.7610
2.500 0.9962 0.01739 0.00923 -0.1659 0.6732 0.7770
2.750 1.0231 0.01740 0.00923 -0.1654 0.6646 0.7941
3.000 1.0453 0.01751 0.00944 -0.1641 0.6531 0.8123
3.250 1.0683 0.01756 0.00954 -0.1629 0.6415 0.8326
3.500 1.0902 0.01753 0.00955 -0.1613 0.6297 0.8566
3.750 1.1092 0.01750 0.00957 -0.1592 0.6172 0.8935
4.000 1.1312 0.01753 0.00968 -0.1579 0.6039 1.0000
4.250 1.1596 0.01778 0.00992 -0.1581 0.5909 1.0000
4.500 1.1876 0.01804 0.01015 -0.1582 0.5781 1.0000
4.750 1.2150 0.01830 0.01041 -0.1581 0.5651 1.0000
5.000 1.2417 0.01858 0.01067 -0.1579 0.5516 1.0000
5.250 1.2670 0.01890 0.01101 -0.1575 0.5370 1.0000
5.500 1.2920 0.01925 0.01138 -0.1570 0.5224 1.0000
5.750 1.3163 0.01961 0.01175 -0.1564 0.5071 1.0000
6.000 1.3395 0.02000 0.01211 -0.1556 0.4895 1.0000
6.250 1.3608 0.02044 0.01250 -0.1544 0.4687 1.0000
6.500 1.3808 0.02095 0.01297 -0.1531 0.4463 1.0000
6.750 1.4004 0.02152 0.01346 -0.1517 0.4252 1.0000
7.000 1.4199 0.02212 0.01404 -0.1503 0.4065 1.0000
7.250 1.4385 0.02275 0.01470 -0.1489 0.3874 1.0000
7.500 1.4558 0.02343 0.01539 -0.1473 0.3674 1.0000
7.750 1.4715 0.02417 0.01613 -0.1454 0.3469 1.0000
8.000 1.4853 0.02499 0.01692 -0.1433 0.3258 1.0000
8.250 1.4959 0.02589 0.01778 -0.1408 0.3026 1.0000
8.500 1.5033 0.02695 0.01877 -0.1379 0.2796 1.0000
8.750 1.5102 0.02812 0.01988 -0.1350 0.2566 1.0000
9.000 1.5153 0.02947 0.02113 -0.1321 0.2358 1.0000
9.250 1.5208 0.03089 0.02251 -0.1295 0.2164 1.0000
9.500 1.5263 0.03239 0.02400 -0.1270 0.1988 1.0000
9.750 1.5313 0.03401 0.02564 -0.1247 0.1825 1.0000
10.000 1.5358 0.03575 0.02738 -0.1225 0.1675 1.0000
10.250 1.5398 0.03761 0.02927 -0.1205 0.1541 1.0000
10.500 1.5427 0.03964 0.03131 -0.1185 0.1423 1.0000
10.750 1.5449 0.04184 0.03352 -0.1167 0.1317 1.0000
11.000 1.5483 0.04402 0.03577 -0.1151 0.1223 1.0000
11.250 1.5497 0.04646 0.03824 -0.1136 0.1148 1.0000
11.500 1.5517 0.04893 0.04081 -0.1123 0.1078 1.0000
11.750 1.5522 0.05163 0.04356 -0.1111 0.1024 1.0000
12.000 1.5549 0.05421 0.04626 -0.1100 0.0971 1.0000
12.250 1.5543 0.05719 0.04929 -0.1090 0.0929 1.0000
12.500 1.5561 0.06002 0.05222 -0.1082 0.0889 1.0000
12.750 1.5583 0.06285 0.05520 -0.1075 0.0847 1.0000
13.000 1.5582 0.06601 0.05842 -0.1070 0.0813 1.0000
13.250 1.5588 0.06916 0.06163 -0.1065 0.0782 1.0000
13.500 1.5621 0.07209 0.06477 -0.1061 0.0749 1.0000
13.750 1.5636 0.07528 0.06809 -0.1059 0.0718 1.0000
14.000 1.5633 0.07872 0.07160 -0.1059 0.0690 1.0000
14.250 1.5642 0.08211 0.07509 -0.1059 0.0662 1.0000
14.500 1.5649 0.08565 0.07886 -0.1062 0.0633 1.0000
14.750 1.5640 0.08944 0.08281 -0.1068 0.0605 1.0000
15.000 1.5621 0.09339 0.08685 -0.1076 0.0583 1.0000
15.250 1.5613 0.09722 0.09077 -0.1083 0.0561 1.0000
15.500 1.5594 0.10148 0.09530 -0.1093 0.0538 1.0000
15.750 1.5567 0.10585 0.09987 -0.1106 0.0515 1.0000
16.000 1.5537 0.11030 0.10445 -0.1122 0.0496 1.0000
16.250 1.5505 0.11478 0.10900 -0.1140 0.0479 1.0000
16.500 1.5473 0.11940 0.11379 -0.1157 0.0462 1.0000
16.750 1.5418 0.12467 0.11932 -0.1181 0.0444 1.0000
17.000 1.5357 0.13010 0.12494 -0.1208 0.0427 1.0000
17.250 1.5312 0.13520 0.13017 -0.1235 0.0412 1.0000
17.500 1.5281 0.13998 0.13502 -0.1262 0.0398 1.0000
17.750 1.5231 0.14528 0.14043 -0.1292 0.0385 1.0000
18.000 1.5131 0.15202 0.14744 -0.1332 0.0375 1.0000
18.250 1.5013 0.15939 0.15506 -0.1381 0.0364 1.0000
18.500 1.4898 0.16687 0.16274 -0.1432 0.0355 1.0000
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