GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 50,000 Max Cl/Cd: 25.88 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe228-il-50000-n5.txt Download as CSV file: xf-goe228-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 228 (MVA H.38) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1237 0.11354 0.10672 -0.0828 0.9334 0.0836
-9.500 -0.1163 0.10930 0.10248 -0.0863 0.9274 0.0842
-9.250 -0.1127 0.10525 0.09842 -0.0892 0.9207 0.0848
-9.000 -0.1126 0.10135 0.09453 -0.0914 0.9125 0.0851
-8.750 -0.1056 0.09627 0.08943 -0.0960 0.9076 0.0850
-8.500 -0.1163 0.09309 0.08631 -0.0958 0.8963 0.0847
-8.250 -0.1203 0.08822 0.08144 -0.0989 0.8889 0.0845
-8.000 -0.1378 0.08394 0.07721 -0.0996 0.8776 0.0844
-7.500 -0.1851 0.06395 0.05692 -0.1201 0.8549 0.0843
-7.250 -0.1814 0.05576 0.04811 -0.1313 0.8443 0.0860
-7.000 -0.1420 0.04941 0.04088 -0.1421 0.8402 0.0887
-6.750 -0.1292 0.04801 0.03940 -0.1413 0.8289 0.0902
-6.500 -0.0910 0.04586 0.03705 -0.1448 0.8244 0.0937
-6.250 -0.0689 0.04426 0.03515 -0.1459 0.8147 0.0976
-6.000 -0.0323 0.04228 0.03285 -0.1488 0.8088 0.1023
-5.750 0.0094 0.04068 0.03114 -0.1517 0.8052 0.1075
-5.500 0.0268 0.03992 0.03015 -0.1510 0.7934 0.1129
-5.250 0.0665 0.03861 0.02883 -0.1534 0.7888 0.1216
-5.000 0.0889 0.03794 0.02802 -0.1534 0.7786 0.1299
-4.750 0.1264 0.03681 0.02682 -0.1555 0.7726 0.1441
-4.500 0.1704 0.03553 0.02562 -0.1587 0.7689 0.1654
-4.250 0.1873 0.03539 0.02560 -0.1578 0.7564 0.1847
-4.000 0.2297 0.03458 0.02494 -0.1603 0.7520 0.2260
-3.750 0.2484 0.03488 0.02529 -0.1593 0.7399 0.2597
-3.500 0.2869 0.03464 0.02498 -0.1605 0.7349 0.2999
-3.250 0.3053 0.03505 0.02530 -0.1592 0.7232 0.3245
-3.000 0.3429 0.03470 0.02476 -0.1603 0.7179 0.3525
-2.750 0.3609 0.03512 0.02512 -0.1589 0.7067 0.3717
-2.500 0.3935 0.03497 0.02494 -0.1588 0.7011 0.3973
-2.250 0.4110 0.03540 0.02535 -0.1571 0.6902 0.4157
-2.000 0.4447 0.03506 0.02491 -0.1573 0.6846 0.4346
-1.750 0.4662 0.03527 0.02501 -0.1566 0.6746 0.4477
-1.500 0.5008 0.03488 0.02444 -0.1575 0.6684 0.4628
-1.250 0.5230 0.03502 0.02455 -0.1563 0.6598 0.4726
-1.000 0.5537 0.03483 0.02421 -0.1567 0.6524 0.4848
-0.750 0.5942 0.03417 0.02336 -0.1582 0.6483 0.4974
-0.500 0.6082 0.03484 0.02400 -0.1566 0.6369 0.5054
-0.250 0.6488 0.03424 0.02317 -0.1583 0.6322 0.5185
0.000 0.6635 0.03490 0.02383 -0.1567 0.6219 0.5263
0.250 0.6998 0.03454 0.02330 -0.1578 0.6165 0.5393
0.500 0.7218 0.03493 0.02362 -0.1572 0.6083 0.5501
0.750 0.7493 0.03503 0.02363 -0.1572 0.6013 0.5622
1.000 0.7888 0.03452 0.02296 -0.1586 0.5970 0.5777
1.250 0.7993 0.03562 0.02406 -0.1569 0.5869 0.5905
1.500 0.8327 0.03542 0.02377 -0.1575 0.5818 0.6065
1.750 0.8562 0.03579 0.02410 -0.1571 0.5752 0.6225
2.000 0.8729 0.03648 0.02480 -0.1559 0.5675 0.6387
2.250 0.9090 0.03620 0.02442 -0.1569 0.5631 0.6607
2.500 0.9197 0.03725 0.02552 -0.1550 0.5556 0.6788
2.750 0.9376 0.03784 0.02616 -0.1538 0.5493 0.6998
3.000 0.9718 0.03755 0.02585 -0.1545 0.5454 0.7276
3.250 0.9771 0.03882 0.02723 -0.1519 0.5384 0.7514
3.500 0.9873 0.03975 0.02829 -0.1498 0.5319 0.7829
3.750 1.0116 0.03934 0.02801 -0.1486 0.5282 0.8478
4.000 1.0196 0.04063 0.02931 -0.1468 0.5222 1.0000
4.250 1.0194 0.04316 0.03185 -0.1450 0.5145 1.0000
4.500 1.0511 0.04355 0.03210 -0.1459 0.5111 1.0000
4.750 1.0910 0.04338 0.03177 -0.1475 0.5087 1.0000
5.000 1.0410 0.04977 0.03839 -0.1419 0.4967 1.0000
5.250 1.0689 0.05024 0.03875 -0.1422 0.4935 1.0000
5.500 1.1045 0.05008 0.03848 -0.1430 0.4914 1.0000
6.000 1.0583 0.06049 0.04909 -0.1381 0.4748 1.0000
6.250 1.0874 0.06075 0.04928 -0.1382 0.4731 1.0000
6.750 1.0119 0.07686 0.06566 -0.1355 0.4532 1.0000
7.250 0.9842 0.08810 0.07703 -0.1350 0.4409 1.0000
7.750 0.9631 0.09834 0.08737 -0.1348 0.4309 1.0000
8.250 0.9759 0.10437 0.09346 -0.1347 0.4247 1.0000
8.500 0.9909 0.10639 0.09549 -0.1346 0.4228 1.0000
8.750 1.0122 0.10758 0.09668 -0.1344 0.4212 1.0000
9.000 0.9763 0.11550 0.10472 -0.1349 0.4136 1.0000
9.250 0.9857 0.11785 0.10711 -0.1347 0.4094 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 228 (MVA H.38) AIRFOIL (goe228-il)