GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 500,000 Max Cl/Cd: 118.07 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe239-il-500000.txt Download as CSV file: xf-goe239-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2127 0.09229 0.09003 -0.0577 0.9857 0.0332
-8.750 -0.2087 0.08417 0.08191 -0.0700 0.9753 0.0359
-8.500 -0.1992 0.07910 0.07684 -0.0734 0.9678 0.0365
-8.250 -0.1792 0.07746 0.07518 -0.0742 0.9606 0.0371
-8.000 -0.1623 0.07523 0.07294 -0.0759 0.9507 0.0379
-7.750 -0.1497 0.07234 0.07002 -0.0785 0.9396 0.0390
-7.500 -0.1509 0.02529 0.02156 -0.1426 0.9169 0.0348
-7.250 -0.1233 0.02201 0.01769 -0.1453 0.9111 0.0356
-7.000 -0.0970 0.01922 0.01446 -0.1470 0.9047 0.0365
-6.750 -0.0698 0.01823 0.01338 -0.1474 0.8990 0.0376
-6.500 -0.0421 0.01751 0.01255 -0.1477 0.8933 0.0384
-6.250 -0.0143 0.01660 0.01149 -0.1480 0.8871 0.0393
-6.000 0.0141 0.01573 0.01041 -0.1482 0.8813 0.0402
-5.750 0.0422 0.01506 0.00958 -0.1484 0.8746 0.0413
-5.500 0.0706 0.01451 0.00887 -0.1484 0.8679 0.0422
-5.250 0.0991 0.01385 0.00804 -0.1485 0.8615 0.0428
-5.000 0.1272 0.01266 0.00677 -0.1488 0.8544 0.0440
-4.750 0.1556 0.01219 0.00623 -0.1488 0.8478 0.0452
-4.500 0.1840 0.01184 0.00585 -0.1489 0.8394 0.0467
-4.250 0.2125 0.01150 0.00542 -0.1488 0.8315 0.0482
-4.000 0.2410 0.01113 0.00499 -0.1488 0.8213 0.0494
-3.750 0.2695 0.01087 0.00464 -0.1487 0.8111 0.0505
-3.500 0.2982 0.01029 0.00400 -0.1488 0.7997 0.0529
-3.250 0.3266 0.01004 0.00371 -0.1487 0.7854 0.0555
-3.000 0.3547 0.00988 0.00346 -0.1486 0.7679 0.0586
-2.750 0.3829 0.00962 0.00311 -0.1485 0.7445 0.0624
-2.500 0.4103 0.00951 0.00288 -0.1482 0.7133 0.0681
-2.250 0.4370 0.00947 0.00265 -0.1478 0.6753 0.0766
-2.000 0.4638 0.00948 0.00251 -0.1475 0.6431 0.0902
-1.750 0.4911 0.00944 0.00238 -0.1473 0.6213 0.1122
-1.500 0.5189 0.00927 0.00240 -0.1475 0.6056 0.1987
-1.250 0.5465 0.00936 0.00245 -0.1474 0.5932 0.2282
-1.000 0.5746 0.00943 0.00249 -0.1473 0.5832 0.2470
-0.750 0.6023 0.00954 0.00255 -0.1472 0.5748 0.2617
-0.500 0.6305 0.00961 0.00260 -0.1472 0.5672 0.2758
0.000 0.6865 0.00979 0.00274 -0.1471 0.5527 0.3020
0.250 0.7143 0.00989 0.00281 -0.1470 0.5459 0.3140
0.500 0.7424 0.00997 0.00289 -0.1470 0.5405 0.3275
0.750 0.7707 0.01002 0.00297 -0.1470 0.5355 0.3419
1.000 0.7987 0.01011 0.00305 -0.1470 0.5309 0.3557
1.250 0.8266 0.01024 0.00316 -0.1469 0.5263 0.3706
1.500 0.8549 0.01026 0.00324 -0.1470 0.5218 0.3872
1.750 0.8830 0.01030 0.00333 -0.1470 0.5170 0.4047
2.000 0.9107 0.01038 0.00342 -0.1469 0.5124 0.4224
2.250 0.9387 0.01044 0.00354 -0.1470 0.5083 0.4432
2.500 0.9669 0.01040 0.00365 -0.1471 0.5038 0.4780
2.750 0.9922 0.00977 0.00388 -0.1467 0.4994 0.7951
3.000 1.0147 0.00968 0.00391 -0.1452 0.4950 1.0000
3.250 1.0425 0.00980 0.00403 -0.1452 0.4906 1.0000
3.500 1.0703 0.00990 0.00414 -0.1451 0.4856 1.0000
3.750 1.0977 0.01005 0.00425 -0.1450 0.4805 1.0000
4.000 1.1249 0.01022 0.00440 -0.1449 0.4753 1.0000
4.250 1.1523 0.01030 0.00451 -0.1447 0.4690 1.0000
4.500 1.1788 0.01047 0.00462 -0.1445 0.4616 1.0000
4.750 1.2059 0.01054 0.00474 -0.1443 0.4532 1.0000
5.000 1.2321 0.01072 0.00487 -0.1440 0.4452 1.0000
5.250 1.2590 0.01081 0.00500 -0.1438 0.4359 1.0000
5.500 1.2850 0.01097 0.00515 -0.1434 0.4255 1.0000
5.750 1.3107 0.01115 0.00530 -0.1430 0.4146 1.0000
6.000 1.3366 0.01132 0.00549 -0.1427 0.4034 1.0000
6.250 1.3618 0.01155 0.00570 -0.1422 0.3914 1.0000
6.500 1.3864 0.01182 0.00593 -0.1417 0.3781 1.0000
6.750 1.4102 0.01213 0.00620 -0.1410 0.3637 1.0000
7.000 1.4335 0.01249 0.00650 -0.1403 0.3489 1.0000
7.250 1.4563 0.01287 0.00685 -0.1395 0.3347 1.0000
7.750 1.5006 0.01371 0.00760 -0.1377 0.3073 1.0000
8.000 1.5219 0.01417 0.00801 -0.1367 0.2925 1.0000
8.250 1.5430 0.01462 0.00843 -0.1356 0.2781 1.0000
8.500 1.5633 0.01511 0.00887 -0.1345 0.2635 1.0000
8.750 1.5831 0.01561 0.00934 -0.1332 0.2490 1.0000
9.000 1.6022 0.01613 0.00984 -0.1319 0.2348 1.0000
9.250 1.6194 0.01674 0.01039 -0.1303 0.2184 1.0000
9.500 1.6343 0.01743 0.01101 -0.1282 0.1981 1.0000
9.750 1.6404 0.01849 0.01186 -0.1248 0.1598 1.0000
10.000 1.6357 0.02026 0.01331 -0.1200 0.1152 1.0000
10.250 1.6373 0.02173 0.01466 -0.1164 0.0922 1.0000
10.500 1.6386 0.02328 0.01608 -0.1129 0.0700 1.0000
10.750 1.6431 0.02470 0.01747 -0.1101 0.0609 1.0000
11.000 1.6504 0.02598 0.01879 -0.1078 0.0562 1.0000
11.250 1.6536 0.02763 0.02046 -0.1052 0.0514 1.0000
11.500 1.6628 0.02887 0.02180 -0.1034 0.0479 1.0000
11.750 1.6657 0.03068 0.02365 -0.1012 0.0438 1.0000
12.000 1.6718 0.03229 0.02533 -0.0994 0.0397 1.0000
12.250 1.6728 0.03440 0.02746 -0.0974 0.0356 1.0000
12.500 1.6769 0.03632 0.02946 -0.0958 0.0319 1.0000
12.750 1.6745 0.03892 0.03209 -0.0940 0.0290 1.0000
13.000 1.6769 0.04118 0.03443 -0.0927 0.0268 1.0000
13.250 1.6759 0.04387 0.03718 -0.0915 0.0250 1.0000
13.500 1.6686 0.04736 0.04075 -0.0903 0.0236 1.0000
13.750 1.6679 0.05030 0.04381 -0.0895 0.0226 1.0000
14.000 1.6657 0.05353 0.04715 -0.0890 0.0217 1.0000
14.250 1.6611 0.05719 0.05089 -0.0887 0.0208 1.0000
14.500 1.6534 0.06139 0.05518 -0.0886 0.0202 1.0000
14.750 1.6412 0.06633 0.06023 -0.0888 0.0196 1.0000
15.000 1.6328 0.07080 0.06482 -0.0890 0.0192 1.0000
15.250 1.6266 0.07499 0.06913 -0.0892 0.0187 1.0000
15.500 1.6191 0.07938 0.07364 -0.0896 0.0183 1.0000
15.750 1.6112 0.08388 0.07825 -0.0900 0.0179 1.0000
16.000 1.6028 0.08848 0.08295 -0.0906 0.0176 1.0000
16.250 1.5943 0.09311 0.08768 -0.0912 0.0172 1.0000
16.500 1.5856 0.09784 0.09251 -0.0920 0.0169 1.0000
16.750 1.5764 0.10271 0.09745 -0.0929 0.0166 1.0000
17.000 1.5663 0.10771 0.10253 -0.0939 0.0163 1.0000
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