GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 500,000 Max Cl/Cd: 111.41 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe430-il-500000.txt Download as CSV file: xf-goe430-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3692 0.12602 0.12347 -0.0498 1.0000 0.0449
-12.750 -0.7577 0.05414 0.05128 -0.0849 1.0000 0.0434
-12.500 -0.7846 0.04214 0.03891 -0.1034 0.9921 0.0437
-12.250 -0.7566 0.03541 0.03177 -0.1214 0.9851 0.0445
-12.000 -0.7295 0.03112 0.02715 -0.1303 0.9825 0.0457
-11.750 -0.7030 0.02983 0.02587 -0.1323 0.9789 0.0466
-11.500 -0.6718 0.02882 0.02482 -0.1350 0.9758 0.0476
-11.250 -0.6372 0.02772 0.02363 -0.1384 0.9736 0.0488
-11.000 -0.6023 0.02648 0.02224 -0.1419 0.9715 0.0500
-10.750 -0.5674 0.02533 0.02091 -0.1451 0.9695 0.0512
-10.500 -0.5400 0.02468 0.02009 -0.1463 0.9645 0.0520
-10.250 -0.5141 0.02238 0.01756 -0.1485 0.9605 0.0531
-10.000 -0.4849 0.02098 0.01611 -0.1500 0.9576 0.0541
-9.750 -0.4543 0.02014 0.01522 -0.1514 0.9552 0.0551
-9.500 -0.4287 0.01943 0.01443 -0.1517 0.9503 0.0559
-9.250 -0.4010 0.01864 0.01355 -0.1523 0.9461 0.0567
-9.000 -0.3722 0.01788 0.01269 -0.1530 0.9426 0.0575
-8.750 -0.3433 0.01722 0.01193 -0.1536 0.9392 0.0584
-8.500 -0.3171 0.01669 0.01130 -0.1536 0.9337 0.0593
-8.250 -0.2893 0.01613 0.01065 -0.1538 0.9289 0.0599
-8.000 -0.2609 0.01564 0.01005 -0.1540 0.9245 0.0604
-7.750 -0.2345 0.01475 0.00907 -0.1541 0.9191 0.0613
-7.500 -0.2073 0.01396 0.00824 -0.1543 0.9137 0.0625
-7.250 -0.1791 0.01343 0.00767 -0.1546 0.9094 0.0637
-7.000 -0.1508 0.01304 0.00723 -0.1548 0.9048 0.0649
-6.750 -0.1228 0.01266 0.00682 -0.1549 0.8990 0.0663
-6.500 -0.0943 0.01230 0.00639 -0.1550 0.8938 0.0676
-6.250 -0.0655 0.01198 0.00600 -0.1551 0.8890 0.0688
-6.000 -0.0371 0.01170 0.00566 -0.1552 0.8831 0.0698
-5.750 -0.0082 0.01123 0.00516 -0.1555 0.8775 0.0720
-5.500 0.0209 0.01090 0.00479 -0.1557 0.8723 0.0745
-5.250 0.0497 0.01063 0.00451 -0.1558 0.8658 0.0773
-5.000 0.0788 0.01041 0.00424 -0.1559 0.8603 0.0805
-4.750 0.1082 0.01010 0.00395 -0.1562 0.8549 0.0875
-4.500 0.1373 0.00983 0.00375 -0.1564 0.8481 0.0999
-4.250 0.1665 0.00965 0.00362 -0.1566 0.8421 0.1209
-4.000 0.1955 0.00957 0.00354 -0.1566 0.8356 0.1346
-3.750 0.2244 0.00949 0.00345 -0.1567 0.8285 0.1441
-3.500 0.2536 0.00939 0.00330 -0.1568 0.8221 0.1513
-3.250 0.2825 0.00927 0.00320 -0.1569 0.8138 0.1583
-3.000 0.3115 0.00923 0.00307 -0.1569 0.8066 0.1632
-2.750 0.3405 0.00905 0.00292 -0.1570 0.7972 0.1698
-2.500 0.3696 0.00896 0.00279 -0.1571 0.7888 0.1761
-2.250 0.3984 0.00886 0.00268 -0.1572 0.7783 0.1828
-2.000 0.4273 0.00875 0.00257 -0.1572 0.7669 0.1912
-1.750 0.4559 0.00867 0.00247 -0.1572 0.7541 0.2016
-1.500 0.4844 0.00859 0.00240 -0.1572 0.7405 0.2184
-1.250 0.5130 0.00853 0.00238 -0.1573 0.7265 0.2479
-1.000 0.5415 0.00850 0.00237 -0.1573 0.7130 0.2784
-0.750 0.5699 0.00849 0.00237 -0.1573 0.6994 0.3025
-0.500 0.5980 0.00850 0.00237 -0.1572 0.6852 0.3246
-0.250 0.6260 0.00853 0.00239 -0.1571 0.6710 0.3452
0.000 0.6539 0.00858 0.00242 -0.1570 0.6575 0.3644
0.250 0.6818 0.00863 0.00247 -0.1569 0.6442 0.3857
0.500 0.7099 0.00867 0.00255 -0.1569 0.6319 0.4128
0.750 0.7378 0.00874 0.00264 -0.1568 0.6201 0.4414
1.000 0.7653 0.00884 0.00273 -0.1566 0.6076 0.4679
1.250 0.7927 0.00895 0.00283 -0.1564 0.5937 0.4914
1.500 0.8200 0.00904 0.00293 -0.1562 0.5786 0.5140
1.750 0.8472 0.00915 0.00304 -0.1560 0.5638 0.5361
2.000 0.8745 0.00925 0.00316 -0.1557 0.5503 0.5577
2.250 0.9014 0.00938 0.00329 -0.1555 0.5369 0.5805
2.500 0.9282 0.00952 0.00343 -0.1552 0.5237 0.6028
2.750 0.9548 0.00968 0.00358 -0.1548 0.5106 0.6240
3.000 0.9817 0.00983 0.00373 -0.1545 0.4990 0.6437
3.250 1.0083 0.00999 0.00388 -0.1542 0.4883 0.6629
3.750 1.0611 0.01029 0.00421 -0.1535 0.4680 0.7015
4.000 1.0870 0.01046 0.00438 -0.1531 0.4595 0.7220
4.250 1.1134 0.01054 0.00456 -0.1527 0.4512 0.7468
4.500 1.1382 0.01064 0.00475 -0.1520 0.4434 0.7877
4.750 1.1582 0.01043 0.00484 -0.1501 0.4359 1.0000
5.000 1.1841 0.01069 0.00504 -0.1497 0.4276 1.0000
5.250 1.2110 0.01087 0.00522 -0.1495 0.4194 1.0000
5.500 1.2363 0.01115 0.00544 -0.1490 0.4102 1.0000
5.750 1.2625 0.01134 0.00565 -0.1487 0.3998 1.0000
6.000 1.2875 0.01160 0.00587 -0.1482 0.3860 1.0000
6.250 1.3120 0.01189 0.00611 -0.1476 0.3693 1.0000
6.500 1.3348 0.01226 0.00638 -0.1467 0.3436 1.0000
6.750 1.3488 0.01323 0.00693 -0.1445 0.2714 1.0000
7.000 1.3637 0.01418 0.00762 -0.1424 0.2387 1.0000
7.250 1.3827 0.01478 0.00815 -0.1410 0.2251 1.0000
7.500 1.4031 0.01527 0.00861 -0.1398 0.2160 1.0000
7.750 1.4218 0.01583 0.00913 -0.1383 0.2072 1.0000
8.000 1.4419 0.01623 0.00954 -0.1370 0.1999 1.0000
8.250 1.4589 0.01674 0.01003 -0.1351 0.1926 1.0000
8.500 1.4776 0.01717 0.01049 -0.1336 0.1854 1.0000
8.750 1.4950 0.01770 0.01099 -0.1320 0.1764 1.0000
9.000 1.5133 0.01817 0.01147 -0.1305 0.1676 1.0000
9.250 1.5294 0.01878 0.01204 -0.1287 0.1564 1.0000
9.500 1.5444 0.01946 0.01267 -0.1269 0.1416 1.0000
9.750 1.5570 0.02030 0.01342 -0.1248 0.1254 1.0000
10.000 1.5681 0.02125 0.01430 -0.1225 0.1118 1.0000
10.250 1.5784 0.02227 0.01527 -0.1203 0.1023 1.0000
10.500 1.5883 0.02336 0.01633 -0.1181 0.0951 1.0000
10.750 1.5991 0.02441 0.01739 -0.1161 0.0892 1.0000
11.000 1.6074 0.02567 0.01864 -0.1140 0.0834 1.0000
11.250 1.6188 0.02674 0.01975 -0.1122 0.0778 1.0000
11.500 1.6256 0.02818 0.02117 -0.1101 0.0694 1.0000
11.750 1.6273 0.03005 0.02289 -0.1076 0.0436 1.0000
12.000 1.6188 0.03285 0.02556 -0.1045 0.0294 1.0000
12.250 1.6204 0.03493 0.02769 -0.1023 0.0261 1.0000
12.500 1.6217 0.03710 0.02991 -0.1004 0.0242 1.0000
12.750 1.6249 0.03916 0.03206 -0.0987 0.0229 1.0000
13.000 1.6283 0.04126 0.03425 -0.0972 0.0219 1.0000
13.250 1.6293 0.04367 0.03673 -0.0957 0.0210 1.0000
13.500 1.6277 0.04643 0.03958 -0.0943 0.0203 1.0000
13.750 1.6232 0.04964 0.04288 -0.0931 0.0197 1.0000
14.000 1.6251 0.05227 0.04561 -0.0922 0.0193 1.0000
14.250 1.6252 0.05515 0.04860 -0.0915 0.0189 1.0000
14.500 1.6238 0.05830 0.05184 -0.0908 0.0185 1.0000
14.750 1.6211 0.06167 0.05532 -0.0904 0.0181 1.0000
15.000 1.6175 0.06525 0.05900 -0.0900 0.0177 1.0000
15.250 1.6125 0.06908 0.06292 -0.0899 0.0174 1.0000
15.500 1.6054 0.07324 0.06718 -0.0898 0.0171 1.0000
15.750 1.5959 0.07783 0.07187 -0.0900 0.0169 1.0000
16.000 1.5839 0.08286 0.07700 -0.0904 0.0166 1.0000
16.250 1.5718 0.08795 0.08219 -0.0910 0.0164 1.0000
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