GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 200,000 Max Cl/Cd: 81.77 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe239-il-200000.txt Download as CSV file: xf-goe239-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2910 0.11025 0.10689 -0.0325 1.0000 0.0538
-9.000 -0.2991 0.10911 0.10580 -0.0299 1.0000 0.0550
-8.750 -0.3055 0.10756 0.10429 -0.0285 0.9997 0.0564
-8.500 -0.3017 0.10343 0.10018 -0.0414 0.9930 0.0598
-8.250 -0.2950 0.09804 0.09481 -0.0487 0.9863 0.0604
-8.000 -0.2678 0.09402 0.09076 -0.0464 0.9862 0.0616
-7.750 -0.2435 0.09083 0.08754 -0.0485 0.9840 0.0634
-7.500 -0.2285 0.08780 0.08452 -0.0515 0.9780 0.0664
-7.250 -0.2097 0.07960 0.07630 -0.0764 0.9645 0.0715
-7.000 -0.1931 0.07671 0.07342 -0.0718 0.9625 0.0727
-6.750 -0.1664 0.07403 0.07071 -0.0728 0.9600 0.0746
-6.500 -0.1392 0.07058 0.06723 -0.0778 0.9555 0.0780
-6.250 -0.1023 0.06157 0.05812 -0.0985 0.9468 0.0855
-6.000 -0.0738 0.05991 0.05646 -0.0979 0.9450 0.0878
-5.750 -0.0470 0.05694 0.05345 -0.1017 0.9386 0.0919
-5.500 0.0240 0.03101 0.02607 -0.1405 0.9319 0.0733
-5.250 0.0675 0.02650 0.02099 -0.1457 0.9294 0.0685
-5.000 0.0990 0.02377 0.01781 -0.1475 0.9222 0.0679
-4.750 0.1366 0.02194 0.01555 -0.1496 0.9171 0.0695
-4.500 0.1758 0.02033 0.01356 -0.1518 0.9130 0.0705
-4.250 0.2040 0.01934 0.01231 -0.1516 0.9033 0.0713
-4.000 0.2384 0.01751 0.01032 -0.1529 0.8975 0.0735
-3.750 0.2654 0.01685 0.00964 -0.1525 0.8871 0.0767
-3.500 0.2967 0.01614 0.00880 -0.1527 0.8791 0.0800
-3.250 0.3246 0.01556 0.00810 -0.1522 0.8676 0.0829
-3.000 0.3522 0.01470 0.00723 -0.1518 0.8556 0.0871
-2.750 0.3805 0.01419 0.00670 -0.1514 0.8434 0.0942
-2.500 0.4091 0.01354 0.00603 -0.1511 0.8305 0.1031
-2.250 0.4373 0.01298 0.00545 -0.1508 0.8153 0.1174
-2.000 0.4651 0.01238 0.00503 -0.1506 0.7973 0.1566
-1.750 0.4925 0.01218 0.00502 -0.1502 0.7769 0.2499
-1.500 0.5199 0.01225 0.00498 -0.1496 0.7564 0.2854
-1.250 0.5473 0.01233 0.00495 -0.1492 0.7368 0.3078
-1.000 0.5746 0.01245 0.00494 -0.1487 0.7175 0.3257
-0.750 0.6020 0.01256 0.00493 -0.1484 0.7001 0.3415
-0.500 0.6295 0.01268 0.00492 -0.1481 0.6849 0.3564
-0.250 0.6571 0.01281 0.00490 -0.1479 0.6718 0.3706
0.000 0.6846 0.01288 0.00492 -0.1477 0.6593 0.3841
0.250 0.7121 0.01293 0.00493 -0.1475 0.6482 0.3973
0.500 0.7398 0.01300 0.00493 -0.1474 0.6387 0.4116
0.750 0.7673 0.01302 0.00496 -0.1473 0.6289 0.4285
1.000 0.7949 0.01307 0.00500 -0.1472 0.6199 0.4477
1.250 0.8224 0.01307 0.00505 -0.1470 0.6111 0.4696
1.500 0.8495 0.01306 0.00516 -0.1469 0.6029 0.5025
1.750 0.8759 0.01291 0.00532 -0.1466 0.5953 0.5915
2.000 0.8964 0.01237 0.00533 -0.1445 0.5886 1.0000
2.250 0.9243 0.01260 0.00546 -0.1445 0.5813 1.0000
2.500 0.9525 0.01291 0.00563 -0.1445 0.5750 1.0000
2.750 0.9798 0.01313 0.00584 -0.1444 0.5681 1.0000
3.000 1.0076 0.01342 0.00603 -0.1443 0.5617 1.0000
3.250 1.0348 0.01369 0.00629 -0.1442 0.5549 1.0000
3.500 1.0619 0.01395 0.00651 -0.1440 0.5477 1.0000
3.750 1.0893 0.01427 0.00676 -0.1439 0.5412 1.0000
4.000 1.1157 0.01451 0.00704 -0.1436 0.5338 1.0000
4.250 1.1434 0.01484 0.00728 -0.1435 0.5274 1.0000
4.500 1.1691 0.01509 0.00761 -0.1431 0.5198 1.0000
4.750 1.1959 0.01538 0.00786 -0.1429 0.5128 1.0000
5.000 1.2219 0.01568 0.00820 -0.1426 0.5053 1.0000
5.250 1.2479 0.01593 0.00846 -0.1422 0.4974 1.0000
5.500 1.2735 0.01623 0.00879 -0.1418 0.4895 1.0000
5.750 1.2986 0.01644 0.00902 -0.1412 0.4804 1.0000
6.000 1.3230 0.01667 0.00930 -0.1406 0.4708 1.0000
6.250 1.3480 0.01687 0.00945 -0.1400 0.4614 1.0000
6.500 1.3705 0.01700 0.00970 -0.1390 0.4496 1.0000
6.750 1.3935 0.01718 0.00992 -0.1380 0.4383 1.0000
7.000 1.4168 0.01738 0.01011 -0.1372 0.4279 1.0000
7.250 1.4391 0.01760 0.01042 -0.1362 0.4164 1.0000
7.500 1.4616 0.01789 0.01077 -0.1353 0.4056 1.0000
7.750 1.4835 0.01819 0.01108 -0.1342 0.3949 1.0000
8.000 1.5045 0.01852 0.01140 -0.1330 0.3833 1.0000
8.250 1.5248 0.01887 0.01184 -0.1318 0.3709 1.0000
8.500 1.5451 0.01930 0.01231 -0.1305 0.3598 1.0000
8.750 1.5643 0.01977 0.01278 -0.1291 0.3488 1.0000
9.000 1.5813 0.02027 0.01328 -0.1274 0.3354 1.0000
9.500 1.6102 0.02144 0.01445 -0.1232 0.3063 1.0000
9.750 1.6226 0.02208 0.01513 -0.1208 0.2917 1.0000
10.000 1.6327 0.02273 0.01584 -0.1179 0.2779 1.0000
10.250 1.6411 0.02352 0.01668 -0.1150 0.2629 1.0000
10.500 1.6472 0.02449 0.01765 -0.1119 0.2459 1.0000
10.750 1.6523 0.02561 0.01879 -0.1089 0.2233 1.0000
11.000 1.6510 0.02723 0.02033 -0.1055 0.1910 1.0000
11.250 1.6380 0.02989 0.02268 -0.1014 0.1409 1.0000
11.500 1.6223 0.03310 0.02566 -0.0975 0.1133 1.0000
11.750 1.6108 0.03623 0.02873 -0.0945 0.0966 1.0000
12.000 1.6025 0.03927 0.03177 -0.0921 0.0842 1.0000
12.250 1.5949 0.04243 0.03495 -0.0902 0.0756 1.0000
12.500 1.5843 0.04606 0.03863 -0.0885 0.0696 1.0000
12.750 1.5747 0.04980 0.04244 -0.0872 0.0646 1.0000
13.000 1.5584 0.05449 0.04717 -0.0863 0.0610 1.0000
13.250 1.5501 0.05848 0.05130 -0.0857 0.0572 1.0000
13.500 1.5391 0.06295 0.05585 -0.0854 0.0540 1.0000
13.750 1.5234 0.06802 0.06093 -0.0851 0.0515 1.0000
14.000 1.5178 0.07193 0.06498 -0.0848 0.0488 1.0000
14.250 1.5125 0.07584 0.06898 -0.0847 0.0462 1.0000
14.500 1.5065 0.07977 0.07294 -0.0846 0.0441 1.0000
14.750 1.5011 0.08318 0.07632 -0.0837 0.0420 1.0000
15.000 1.5008 0.08657 0.07987 -0.0837 0.0402 1.0000
15.250 1.5001 0.08993 0.08334 -0.0838 0.0383 1.0000
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Polar data table (+)
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