GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.09 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe430-il-1000000.txt Download as CSV file: xf-goe430-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7922 0.11100 0.10882 -0.0523 1.0000 0.0280
-17.250 -0.8308 0.10045 0.09813 -0.0588 1.0000 0.0285
-17.000 -0.8494 0.09367 0.09133 -0.0630 1.0000 0.0292
-16.750 -0.8678 0.08692 0.08453 -0.0674 1.0000 0.0297
-16.500 -0.8885 0.07989 0.07744 -0.0720 1.0000 0.0301
-16.250 -0.9096 0.07292 0.07039 -0.0767 1.0000 0.0305
-16.000 -0.9325 0.06591 0.06329 -0.0816 1.0000 0.0309
-15.750 -0.9556 0.05924 0.05653 -0.0865 1.0000 0.0312
-15.500 -0.9785 0.05273 0.04993 -0.0914 1.0000 0.0314
-15.250 -0.9986 0.04684 0.04395 -0.0957 1.0000 0.0317
-15.000 -1.0254 0.04141 0.03843 -0.0983 1.0000 0.0318
-14.750 -1.0495 0.03629 0.03323 -0.1013 0.9978 0.0320
-14.500 -1.0226 0.03252 0.02933 -0.1095 0.9948 0.0327
-14.250 -0.9913 0.02964 0.02631 -0.1167 0.9925 0.0331
-14.000 -0.9583 0.02500 0.02152 -0.1286 0.9877 0.0343
-13.750 -0.9236 0.02373 0.02020 -0.1329 0.9857 0.0350
-13.500 -0.8898 0.02298 0.01941 -0.1358 0.9837 0.0358
-13.250 -0.8561 0.02231 0.01869 -0.1385 0.9818 0.0366
-13.000 -0.8278 0.02166 0.01796 -0.1399 0.9766 0.0373
-12.750 -0.7977 0.02102 0.01723 -0.1417 0.9725 0.0379
-12.500 -0.7667 0.02047 0.01660 -0.1433 0.9690 0.0384
-12.250 -0.7417 0.01972 0.01575 -0.1440 0.9619 0.0388
-12.000 -0.7168 0.01842 0.01436 -0.1454 0.9560 0.0399
-11.750 -0.6905 0.01792 0.01383 -0.1458 0.9498 0.0406
-11.500 -0.6638 0.01749 0.01336 -0.1462 0.9437 0.0412
-11.250 -0.6367 0.01709 0.01289 -0.1465 0.9384 0.0419
-11.000 -0.6095 0.01670 0.01245 -0.1469 0.9330 0.0426
-10.750 -0.5820 0.01633 0.01200 -0.1473 0.9284 0.0433
-10.500 -0.5539 0.01607 0.01167 -0.1476 0.9243 0.0440
-10.250 -0.5255 0.01591 0.01145 -0.1479 0.9204 0.0446
-10.000 -0.4971 0.01571 0.01119 -0.1482 0.9161 0.0449
-9.750 -0.4715 0.01435 0.00971 -0.1490 0.9115 0.0461
-9.500 -0.4438 0.01377 0.00907 -0.1494 0.9068 0.0468
-9.250 -0.4157 0.01331 0.00858 -0.1498 0.9025 0.0474
-9.000 -0.3874 0.01291 0.00814 -0.1502 0.8980 0.0480
-8.750 -0.3590 0.01257 0.00773 -0.1504 0.8936 0.0487
-8.500 -0.3304 0.01226 0.00737 -0.1507 0.8891 0.0495
-8.250 -0.3016 0.01191 0.00698 -0.1511 0.8849 0.0501
-8.000 -0.2727 0.01159 0.00660 -0.1514 0.8806 0.0507
-7.750 -0.2439 0.01130 0.00625 -0.1516 0.8763 0.0513
-7.500 -0.2149 0.01105 0.00594 -0.1519 0.8720 0.0517
-7.250 -0.1857 0.01080 0.00566 -0.1522 0.8675 0.0521
-7.000 -0.1565 0.01034 0.00514 -0.1526 0.8630 0.0529
-6.750 -0.1273 0.00991 0.00464 -0.1531 0.8584 0.0543
-6.500 -0.0979 0.00962 0.00433 -0.1534 0.8535 0.0556
-6.250 -0.0685 0.00937 0.00405 -0.1537 0.8478 0.0566
-6.000 -0.0393 0.00916 0.00378 -0.1539 0.8420 0.0577
-5.750 -0.0098 0.00897 0.00355 -0.1542 0.8366 0.0587
-5.500 0.0197 0.00879 0.00334 -0.1545 0.8310 0.0597
-5.250 0.0491 0.00865 0.00314 -0.1547 0.8255 0.0605
-5.000 0.0789 0.00841 0.00287 -0.1550 0.8198 0.0628
-4.750 0.1085 0.00820 0.00265 -0.1553 0.8133 0.0655
-4.500 0.1379 0.00805 0.00247 -0.1555 0.8068 0.0685
-4.250 0.1676 0.00787 0.00230 -0.1558 0.7995 0.0740
-4.000 0.1971 0.00764 0.00213 -0.1562 0.7917 0.0923
-3.750 0.2267 0.00748 0.00205 -0.1565 0.7834 0.1172
-3.500 0.2558 0.00742 0.00199 -0.1566 0.7741 0.1286
-3.250 0.2850 0.00739 0.00193 -0.1567 0.7633 0.1342
-3.000 0.3140 0.00735 0.00187 -0.1568 0.7505 0.1405
-2.750 0.3426 0.00736 0.00182 -0.1568 0.7347 0.1451
-2.500 0.3712 0.00740 0.00178 -0.1567 0.7184 0.1484
-2.250 0.3999 0.00737 0.00172 -0.1568 0.7036 0.1549
-2.000 0.4286 0.00739 0.00168 -0.1569 0.6896 0.1596
-1.750 0.4571 0.00744 0.00166 -0.1568 0.6757 0.1629
-1.500 0.4858 0.00745 0.00163 -0.1569 0.6616 0.1686
-1.250 0.5143 0.00747 0.00161 -0.1570 0.6470 0.1755
-1.000 0.5429 0.00748 0.00160 -0.1570 0.6332 0.1872
-0.750 0.5717 0.00743 0.00162 -0.1572 0.6216 0.2158
-0.500 0.6004 0.00741 0.00166 -0.1573 0.6103 0.2564
-0.250 0.6292 0.00743 0.00169 -0.1574 0.5995 0.2789
0.000 0.6577 0.00747 0.00173 -0.1575 0.5882 0.2960
0.250 0.6859 0.00754 0.00178 -0.1575 0.5736 0.3135
0.500 0.7140 0.00761 0.00183 -0.1574 0.5579 0.3298
0.750 0.7420 0.00769 0.00189 -0.1574 0.5422 0.3447
1.000 0.7699 0.00777 0.00195 -0.1574 0.5249 0.3630
1.250 0.7976 0.00786 0.00204 -0.1573 0.5056 0.3901
1.500 0.8252 0.00796 0.00215 -0.1572 0.4881 0.4259
1.750 0.8527 0.00809 0.00227 -0.1571 0.4740 0.4540
2.000 0.8804 0.00820 0.00239 -0.1570 0.4629 0.4779
2.250 0.9083 0.00829 0.00249 -0.1570 0.4542 0.4992
2.500 0.9359 0.00841 0.00261 -0.1568 0.4457 0.5171
2.750 0.9638 0.00850 0.00273 -0.1568 0.4385 0.5340
3.000 0.9911 0.00864 0.00286 -0.1566 0.4292 0.5523
3.250 1.0188 0.00874 0.00299 -0.1565 0.4214 0.5735
3.500 1.0462 0.00885 0.00314 -0.1564 0.4143 0.5957
3.750 1.0737 0.00896 0.00329 -0.1562 0.4081 0.6188
4.000 1.1013 0.00907 0.00343 -0.1561 0.4014 0.6409
4.250 1.1280 0.00924 0.00359 -0.1558 0.3937 0.6581
4.500 1.1556 0.00933 0.00372 -0.1557 0.3860 0.6742
4.750 1.1820 0.00950 0.00389 -0.1554 0.3755 0.6908
5.000 1.2084 0.00966 0.00405 -0.1551 0.3623 0.7082
5.250 1.2340 0.00988 0.00424 -0.1547 0.3411 0.7279
5.500 1.2491 0.01092 0.00485 -0.1526 0.2525 0.7518
5.750 1.2693 0.01126 0.00530 -0.1513 0.2272 0.8479
6.000 1.2887 0.01144 0.00557 -0.1495 0.2145 1.0000
6.250 1.3126 0.01181 0.00587 -0.1488 0.2049 1.0000
6.500 1.3377 0.01207 0.00612 -0.1483 0.1987 1.0000
6.750 1.3612 0.01243 0.00643 -0.1476 0.1904 1.0000
7.000 1.3862 0.01266 0.00666 -0.1471 0.1851 1.0000
7.250 1.4097 0.01300 0.00695 -0.1463 0.1771 1.0000
7.500 1.4334 0.01329 0.00723 -0.1456 0.1698 1.0000
7.750 1.4555 0.01368 0.00756 -0.1447 0.1587 1.0000
8.000 1.4766 0.01412 0.00791 -0.1436 0.1443 1.0000
8.250 1.4945 0.01473 0.00839 -0.1419 0.1218 1.0000
8.500 1.5089 0.01548 0.00899 -0.1397 0.1015 1.0000
8.750 1.5234 0.01607 0.00952 -0.1375 0.0922 1.0000
9.000 1.5398 0.01660 0.01004 -0.1356 0.0877 1.0000
9.250 1.5550 0.01719 0.01061 -0.1335 0.0827 1.0000
9.500 1.5727 0.01766 0.01111 -0.1319 0.0800 1.0000
9.750 1.5894 0.01819 0.01166 -0.1302 0.0770 1.0000
10.000 1.6035 0.01889 0.01234 -0.1282 0.0728 1.0000
10.250 1.6197 0.01947 0.01294 -0.1266 0.0681 1.0000
10.500 1.6313 0.02035 0.01376 -0.1244 0.0568 1.0000
10.750 1.6224 0.02260 0.01576 -0.1197 0.0255 1.0000
11.000 1.6291 0.02392 0.01708 -0.1172 0.0210 1.0000
11.250 1.6389 0.02507 0.01826 -0.1151 0.0190 1.0000
11.500 1.6489 0.02623 0.01946 -0.1132 0.0179 1.0000
11.750 1.6566 0.02759 0.02087 -0.1111 0.0167 1.0000
12.000 1.6662 0.02885 0.02218 -0.1093 0.0161 1.0000
12.250 1.6757 0.03014 0.02352 -0.1076 0.0156 1.0000
12.500 1.6841 0.03154 0.02498 -0.1059 0.0150 1.0000
12.750 1.6910 0.03311 0.02660 -0.1041 0.0145 1.0000
13.000 1.6957 0.03492 0.02847 -0.1023 0.0140 1.0000
13.250 1.6961 0.03716 0.03080 -0.1003 0.0135 1.0000
13.500 1.7030 0.03886 0.03256 -0.0990 0.0133 1.0000
13.750 1.7089 0.04071 0.03448 -0.0977 0.0130 1.0000
14.000 1.7137 0.04274 0.03657 -0.0964 0.0127 1.0000
14.250 1.7175 0.04491 0.03882 -0.0953 0.0124 1.0000
14.500 1.7207 0.04723 0.04120 -0.0942 0.0121 1.0000
14.750 1.7227 0.04975 0.04379 -0.0933 0.0119 1.0000
15.000 1.7227 0.05256 0.04669 -0.0924 0.0116 1.0000
15.250 1.7201 0.05576 0.04997 -0.0917 0.0114 1.0000
15.500 1.7134 0.05954 0.05385 -0.0910 0.0111 1.0000
15.750 1.7028 0.06396 0.05839 -0.0906 0.0109 1.0000
16.000 1.7025 0.06712 0.06163 -0.0904 0.0109 1.0000
16.250 1.7013 0.07043 0.06503 -0.0902 0.0107 1.0000
16.500 1.6980 0.07407 0.06876 -0.0902 0.0106 1.0000
16.750 1.6938 0.07789 0.07267 -0.0903 0.0105 1.0000
17.000 1.6890 0.08187 0.07675 -0.0906 0.0104 1.0000
17.250 1.6828 0.08609 0.08107 -0.0910 0.0102 1.0000
17.500 1.6756 0.09049 0.08557 -0.0915 0.0101 1.0000
17.750 1.6681 0.09502 0.09019 -0.0922 0.0100 1.0000
18.000 1.6602 0.09967 0.09494 -0.0930 0.0099 1.0000
18.250 1.6519 0.10443 0.09980 -0.0940 0.0098 1.0000
18.500 1.6426 0.10938 0.10484 -0.0952 0.0097 1.0000
18.750 1.6334 0.11434 0.10990 -0.0965 0.0096 1.0000
19.000 1.6244 0.11934 0.11499 -0.0980 0.0095 1.0000
19.250 1.6148 0.12450 0.12025 -0.0997 0.0094 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 430 AIRFOIL (goe430-il)