GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 100,000 Max Cl/Cd: 59.74 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe430-il-100000.txt Download as CSV file: xf-goe430-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3452 0.10980 0.10490 -0.0278 1.0000 0.1603
-8.250 -0.3957 0.11099 0.10626 -0.0268 1.0000 0.1630
-8.000 -0.4448 0.11173 0.10716 -0.0246 1.0000 0.1635
-7.750 -0.4024 0.10531 0.10066 -0.0230 1.0000 0.1653
-7.500 -0.3832 0.10275 0.09809 -0.0205 1.0000 0.1681
-7.250 -0.3863 0.10130 0.09669 -0.0182 1.0000 0.1711
-7.000 -0.4005 0.10017 0.09563 -0.0159 1.0000 0.1743
-6.250 -0.3977 0.05908 0.05394 -0.0775 0.9779 0.1325
-6.000 -0.3614 0.05226 0.04683 -0.0866 0.9724 0.1302
-5.750 -0.3102 0.04338 0.03726 -0.1008 0.9693 0.1282
-5.500 -0.2641 0.03790 0.03096 -0.1097 0.9634 0.1298
-5.250 -0.2132 0.03473 0.02724 -0.1167 0.9578 0.1337
-5.000 -0.1701 0.03329 0.02568 -0.1205 0.9499 0.1374
-4.750 -0.1203 0.03155 0.02357 -0.1255 0.9426 0.1427
-4.500 -0.0748 0.03001 0.02168 -0.1296 0.9352 0.1499
-4.250 -0.0336 0.02915 0.02076 -0.1325 0.9277 0.1590
-4.000 0.0161 0.02795 0.01946 -0.1369 0.9239 0.1714
-3.750 0.0458 0.02728 0.01876 -0.1377 0.9141 0.1858
-3.500 0.0918 0.02670 0.01816 -0.1412 0.9090 0.2100
-3.250 0.1233 0.02653 0.01793 -0.1421 0.8998 0.2289
-3.000 0.1649 0.02621 0.01768 -0.1446 0.8936 0.2471
-2.750 0.2017 0.02606 0.01752 -0.1462 0.8863 0.2639
-2.500 0.2378 0.02586 0.01734 -0.1476 0.8781 0.2812
-2.250 0.2860 0.02543 0.01701 -0.1510 0.8745 0.3036
-2.000 0.3107 0.02536 0.01696 -0.1505 0.8631 0.3189
-1.750 0.3556 0.02470 0.01636 -0.1532 0.8590 0.3391
-1.500 0.3836 0.02448 0.01620 -0.1531 0.8488 0.3574
-1.250 0.4240 0.02386 0.01567 -0.1548 0.8432 0.3863
-1.000 0.4542 0.02364 0.01556 -0.1548 0.8341 0.4184
-0.750 0.4896 0.02322 0.01527 -0.1554 0.8270 0.4538
-0.500 0.5199 0.02301 0.01514 -0.1552 0.8182 0.4856
-0.250 0.5526 0.02265 0.01488 -0.1552 0.8104 0.5164
0.000 0.5812 0.02248 0.01481 -0.1547 0.8013 0.5453
0.250 0.6134 0.02214 0.01454 -0.1547 0.7937 0.5760
0.500 0.6400 0.02207 0.01455 -0.1538 0.7837 0.6040
0.750 0.6726 0.02165 0.01418 -0.1536 0.7766 0.6343
1.000 0.6977 0.02157 0.01417 -0.1525 0.7655 0.6650
1.250 0.7310 0.02092 0.01356 -0.1522 0.7590 0.7017
1.500 0.7539 0.02075 0.01346 -0.1506 0.7466 0.7363
1.750 0.7803 0.02026 0.01304 -0.1493 0.7370 0.7757
2.000 0.8047 0.01969 0.01257 -0.1474 0.7276 0.8210
2.250 0.8201 0.01933 0.01243 -0.1441 0.7165 0.9001
2.500 0.8628 0.01896 0.01191 -0.1467 0.7091 1.0000
2.750 0.8928 0.01933 0.01219 -0.1476 0.6973 1.0000
3.000 0.9255 0.01945 0.01220 -0.1485 0.6882 1.0000
3.250 0.9572 0.01955 0.01218 -0.1490 0.6787 1.0000
3.500 0.9849 0.01989 0.01246 -0.1490 0.6685 1.0000
3.750 1.0175 0.01995 0.01242 -0.1495 0.6607 1.0000
4.000 1.0424 0.02042 0.01290 -0.1491 0.6506 1.0000
4.250 1.0747 0.02053 0.01291 -0.1495 0.6436 1.0000
4.500 1.0980 0.02109 0.01352 -0.1489 0.6338 1.0000
4.750 1.1304 0.02110 0.01342 -0.1491 0.6256 1.0000
5.000 1.1532 0.02153 0.01390 -0.1482 0.6143 1.0000
5.250 1.1798 0.02175 0.01411 -0.1477 0.6037 1.0000
5.500 1.2093 0.02181 0.01411 -0.1475 0.5937 1.0000
5.750 1.2316 0.02221 0.01458 -0.1464 0.5822 1.0000
6.000 1.2581 0.02238 0.01475 -0.1458 0.5713 1.0000
6.250 1.2857 0.02247 0.01479 -0.1453 0.5601 1.0000
6.500 1.3069 0.02281 0.01523 -0.1440 0.5476 1.0000
6.750 1.3307 0.02304 0.01551 -0.1430 0.5354 1.0000
7.000 1.3548 0.02316 0.01563 -0.1419 0.5216 1.0000
7.250 1.3769 0.02328 0.01575 -0.1405 0.5057 1.0000
7.500 1.3973 0.02346 0.01595 -0.1388 0.4883 1.0000
7.750 1.4164 0.02371 0.01622 -0.1370 0.4696 1.0000
8.000 1.4345 0.02404 0.01653 -0.1350 0.4494 1.0000
8.250 1.4523 0.02445 0.01685 -0.1330 0.4281 1.0000
8.500 1.4647 0.02507 0.01750 -0.1303 0.4043 1.0000
8.750 1.4766 0.02573 0.01813 -0.1275 0.3808 1.0000
9.000 1.4873 0.02647 0.01882 -0.1247 0.3585 1.0000
9.250 1.4963 0.02727 0.01963 -0.1217 0.3374 1.0000
9.500 1.5034 0.02812 0.02042 -0.1184 0.3193 1.0000
9.750 1.5101 0.02910 0.02133 -0.1153 0.3028 1.0000
10.000 1.5166 0.03024 0.02236 -0.1123 0.2872 1.0000
10.250 1.5233 0.03154 0.02353 -0.1095 0.2720 1.0000
10.500 1.5307 0.03298 0.02484 -0.1069 0.2571 1.0000
10.750 1.5390 0.03450 0.02625 -0.1046 0.2427 1.0000
11.000 1.5477 0.03606 0.02775 -0.1024 0.2292 1.0000
11.250 1.5585 0.03759 0.02920 -0.1006 0.2173 1.0000
11.500 1.5707 0.03902 0.03056 -0.0989 0.2066 1.0000
11.750 1.5747 0.04064 0.03235 -0.0965 0.1978 1.0000
12.000 1.5892 0.04198 0.03356 -0.0952 0.1891 1.0000
12.250 1.5869 0.04376 0.03564 -0.0924 0.1823 1.0000
12.500 1.5922 0.04526 0.03715 -0.0904 0.1752 1.0000
12.750 1.5895 0.04723 0.03935 -0.0881 0.1684 1.0000
13.000 1.5872 0.04916 0.04138 -0.0860 0.1617 1.0000
13.250 1.5840 0.05136 0.04374 -0.0842 0.1552 1.0000
13.500 1.5795 0.05377 0.04633 -0.0826 0.1484 1.0000
13.750 1.5742 0.05641 0.04907 -0.0812 0.1417 1.0000
14.000 1.5656 0.05953 0.05237 -0.0802 0.1340 1.0000
14.250 1.5559 0.06307 0.05605 -0.0795 0.1255 1.0000
14.500 1.5438 0.06711 0.06009 -0.0792 0.1165 1.0000
14.750 1.5295 0.07179 0.06486 -0.0793 0.1061 1.0000
15.000 1.5146 0.07680 0.06990 -0.0795 0.0954 1.0000
15.250 1.5009 0.08173 0.07481 -0.0795 0.0858 1.0000
15.500 1.4908 0.08617 0.07920 -0.0793 0.0783 1.0000
15.750 1.4843 0.09026 0.08330 -0.0793 0.0725 1.0000
16.000 1.4804 0.09400 0.08710 -0.0791 0.0680 1.0000
16.250 1.4767 0.09790 0.09112 -0.0794 0.0642 1.0000
16.500 1.4771 0.10095 0.09408 -0.0794 0.0611 1.0000
16.750 1.4733 0.10508 0.09843 -0.0800 0.0587 1.0000
17.000 1.4702 0.10909 0.10262 -0.0808 0.0563 1.0000
17.250 1.4693 0.11268 0.10626 -0.0816 0.0543 1.0000
17.500 1.4767 0.11455 0.10803 -0.0812 0.0524 1.0000
17.750 1.4728 0.11888 0.11260 -0.0822 0.0513 1.0000
18.000 1.4676 0.12353 0.11749 -0.0837 0.0503 1.0000
18.250 1.4610 0.12853 0.12271 -0.0856 0.0495 1.0000
18.500 1.4526 0.13399 0.12838 -0.0880 0.0489 1.0000
18.750 1.4412 0.14020 0.13481 -0.0912 0.0484 1.0000
19.000 1.4248 0.14773 0.14258 -0.0957 0.0481 1.0000
19.250 1.3950 0.15881 0.15399 -0.1031 0.0485 1.0000
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Polar data table (+)
Polar graphs
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