GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 500,000 Max Cl/Cd: 88.22 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe228-il-500000-n5.txt Download as CSV file: xf-goe228-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4264 0.09326 0.09031 -0.0990 0.9649 0.0219
-15.500 -0.4625 0.08280 0.07968 -0.1057 0.9575 0.0221
-15.250 -0.4824 0.07571 0.07246 -0.1102 0.9492 0.0223
-15.000 -0.4976 0.06968 0.06631 -0.1140 0.9407 0.0224
-14.750 -0.5083 0.06452 0.06105 -0.1175 0.9310 0.0226
-14.500 -0.5174 0.05982 0.05622 -0.1206 0.9216 0.0228
-14.250 -0.5247 0.05546 0.05176 -0.1237 0.9113 0.0230
-14.000 -0.5307 0.05142 0.04759 -0.1267 0.9015 0.0232
-13.750 -0.5349 0.04764 0.04368 -0.1296 0.8916 0.0235
-13.500 -0.5366 0.04405 0.03997 -0.1326 0.8819 0.0237
-13.250 -0.5364 0.04067 0.03644 -0.1356 0.8732 0.0240
-13.000 -0.5332 0.03748 0.03312 -0.1388 0.8643 0.0243
-12.750 -0.5289 0.03451 0.02998 -0.1418 0.8564 0.0247
-12.500 -0.5189 0.03170 0.02703 -0.1458 0.8485 0.0250
-12.250 -0.5017 0.02914 0.02426 -0.1503 0.8410 0.0253
-12.000 -0.4809 0.02678 0.02179 -0.1550 0.8336 0.0257
-11.750 -0.4558 0.02478 0.01968 -0.1595 0.8267 0.0261
-11.500 -0.4278 0.02320 0.01798 -0.1634 0.8215 0.0266
-11.250 -0.4001 0.02207 0.01676 -0.1660 0.8165 0.0271
-11.000 -0.3727 0.02114 0.01574 -0.1679 0.8115 0.0277
-10.750 -0.3453 0.02031 0.01478 -0.1695 0.8068 0.0282
-10.500 -0.3174 0.01954 0.01390 -0.1708 0.8025 0.0287
-10.250 -0.2893 0.01886 0.01312 -0.1720 0.7977 0.0292
-10.000 -0.2610 0.01824 0.01238 -0.1730 0.7928 0.0297
-9.750 -0.2330 0.01746 0.01155 -0.1742 0.7881 0.0303
-9.500 -0.2042 0.01686 0.01091 -0.1753 0.7836 0.0309
-9.250 -0.1753 0.01633 0.01032 -0.1762 0.7784 0.0314
-9.000 -0.1462 0.01586 0.00977 -0.1770 0.7731 0.0321
-8.750 -0.1171 0.01543 0.00926 -0.1777 0.7683 0.0328
-8.500 -0.0876 0.01501 0.00878 -0.1785 0.7629 0.0335
-8.250 -0.0582 0.01461 0.00830 -0.1792 0.7571 0.0340
-8.000 -0.0287 0.01417 0.00778 -0.1799 0.7514 0.0347
-7.750 0.0011 0.01373 0.00731 -0.1808 0.7452 0.0354
-7.500 0.0307 0.01339 0.00691 -0.1814 0.7383 0.0363
-7.250 0.0603 0.01310 0.00655 -0.1820 0.7315 0.0373
-7.000 0.0900 0.01282 0.00621 -0.1825 0.7232 0.0384
-6.750 0.1194 0.01258 0.00588 -0.1830 0.7149 0.0393
-6.500 0.1492 0.01228 0.00554 -0.1836 0.7052 0.0407
-6.250 0.1785 0.01206 0.00525 -0.1841 0.6948 0.0423
-6.000 0.2076 0.01189 0.00499 -0.1844 0.6828 0.0442
-5.750 0.2368 0.01171 0.00476 -0.1848 0.6700 0.0468
-5.500 0.2656 0.01158 0.00456 -0.1851 0.6568 0.0508
-5.250 0.2941 0.01148 0.00440 -0.1853 0.6428 0.0565
-5.000 0.3225 0.01141 0.00426 -0.1855 0.6287 0.0630
-4.750 0.3507 0.01138 0.00413 -0.1857 0.6147 0.0689
-4.500 0.3792 0.01133 0.00401 -0.1859 0.6013 0.0747
-4.250 0.4075 0.01131 0.00391 -0.1860 0.5892 0.0797
-4.000 0.4357 0.01128 0.00381 -0.1862 0.5775 0.0856
-3.750 0.4641 0.01124 0.00371 -0.1864 0.5659 0.0934
-3.500 0.4926 0.01116 0.00363 -0.1867 0.5554 0.1093
-3.250 0.5211 0.01105 0.00356 -0.1871 0.5452 0.1433
-3.000 0.5500 0.01092 0.00349 -0.1876 0.5368 0.1783
-2.750 0.5785 0.01083 0.00350 -0.1879 0.5281 0.2260
-2.500 0.6068 0.01085 0.00354 -0.1881 0.5203 0.2558
-2.250 0.6346 0.01092 0.00359 -0.1882 0.5119 0.2750
-2.000 0.6623 0.01101 0.00365 -0.1882 0.5045 0.2879
-1.750 0.6902 0.01110 0.00369 -0.1882 0.4969 0.2953
-1.250 0.7455 0.01129 0.00380 -0.1882 0.4843 0.3109
-1.000 0.7730 0.01138 0.00387 -0.1882 0.4780 0.3174
-0.750 0.7999 0.01151 0.00395 -0.1881 0.4722 0.3247
-0.500 0.8276 0.01160 0.00401 -0.1881 0.4666 0.3310
-0.250 0.8546 0.01171 0.00410 -0.1881 0.4603 0.3375
0.000 0.8809 0.01185 0.00421 -0.1879 0.4538 0.3453
0.250 0.9079 0.01196 0.00430 -0.1878 0.4468 0.3536
0.500 0.9337 0.01212 0.00442 -0.1875 0.4397 0.3612
0.750 0.9602 0.01226 0.00453 -0.1873 0.4343 0.3683
1.000 0.9868 0.01236 0.00465 -0.1872 0.4292 0.3754
1.250 1.0125 0.01252 0.00478 -0.1869 0.4242 0.3820
1.750 1.0644 0.01279 0.00505 -0.1865 0.4156 0.3962
2.000 1.0897 0.01295 0.00520 -0.1861 0.4104 0.4052
2.250 1.1136 0.01315 0.00539 -0.1856 0.4047 0.4148
2.750 1.1633 0.01346 0.00574 -0.1848 0.3942 0.4385
3.000 1.1861 0.01366 0.00596 -0.1840 0.3894 0.4540
3.250 1.2081 0.01385 0.00618 -0.1831 0.3855 0.4736
3.500 1.2310 0.01400 0.00641 -0.1823 0.3817 0.4978
3.750 1.2536 0.01421 0.00667 -0.1815 0.3776 0.5225
4.000 1.2759 0.01447 0.00695 -0.1807 0.3738 0.5433
4.250 1.2975 0.01477 0.00726 -0.1798 0.3702 0.5592
4.500 1.3211 0.01499 0.00752 -0.1793 0.3673 0.5727
4.750 1.3441 0.01524 0.00781 -0.1787 0.3640 0.5841
5.000 1.3663 0.01552 0.00811 -0.1779 0.3606 0.5941
5.250 1.3876 0.01585 0.00846 -0.1771 0.3573 0.6043
5.500 1.4082 0.01621 0.00883 -0.1761 0.3541 0.6139
5.750 1.4300 0.01652 0.00917 -0.1753 0.3515 0.6237
6.000 1.4521 0.01682 0.00952 -0.1747 0.3488 0.6324
6.250 1.4734 0.01715 0.00990 -0.1739 0.3458 0.6411
6.500 1.4941 0.01752 0.01031 -0.1730 0.3428 0.6494
6.750 1.5137 0.01794 0.01076 -0.1720 0.3399 0.6593
7.000 1.5328 0.01840 0.01125 -0.1710 0.3371 0.6697
7.250 1.5534 0.01879 0.01170 -0.1702 0.3349 0.6810
7.500 1.5740 0.01917 0.01216 -0.1694 0.3324 0.6935
7.750 1.5939 0.01958 0.01265 -0.1686 0.3295 0.7092
8.000 1.6126 0.02006 0.01322 -0.1676 0.3255 0.7359
8.250 1.6241 0.02029 0.01378 -0.1652 0.3221 1.0000
8.500 1.6415 0.02090 0.01441 -0.1641 0.3191 1.0000
8.750 1.6608 0.02142 0.01497 -0.1633 0.3164 1.0000
9.000 1.6793 0.02199 0.01558 -0.1624 0.3135 1.0000
9.250 1.6967 0.02263 0.01626 -0.1614 0.3104 1.0000
9.500 1.7126 0.02338 0.01702 -0.1603 0.3070 1.0000
9.750 1.7266 0.02424 0.01789 -0.1589 0.3031 1.0000
10.000 1.7436 0.02494 0.01863 -0.1580 0.2982 1.0000
10.250 1.7568 0.02589 0.01960 -0.1567 0.2917 1.0000
10.500 1.7688 0.02695 0.02066 -0.1552 0.2859 1.0000
10.750 1.7829 0.02787 0.02162 -0.1541 0.2795 1.0000
11.000 1.7916 0.02919 0.02293 -0.1525 0.2721 1.0000
11.250 1.8007 0.03052 0.02427 -0.1509 0.2611 1.0000
11.500 1.8042 0.03232 0.02602 -0.1490 0.2460 1.0000
11.750 1.7903 0.03562 0.02915 -0.1457 0.2114 1.0000
12.000 1.7645 0.04015 0.03348 -0.1418 0.1782 1.0000
12.250 1.7603 0.04295 0.03629 -0.1399 0.1701 1.0000
12.500 1.7571 0.04575 0.03912 -0.1381 0.1639 1.0000
12.750 1.7581 0.04824 0.04166 -0.1368 0.1603 1.0000
13.000 1.7577 0.05094 0.04442 -0.1356 0.1569 1.0000
13.250 1.7557 0.05387 0.04741 -0.1343 0.1538 1.0000
13.500 1.7531 0.05694 0.05054 -0.1332 0.1510 1.0000
13.750 1.7524 0.05985 0.05353 -0.1323 0.1486 1.0000
14.000 1.7548 0.06247 0.05624 -0.1316 0.1464 1.0000
14.250 1.7545 0.06543 0.05929 -0.1308 0.1439 1.0000
14.500 1.7524 0.06865 0.06260 -0.1302 0.1416 1.0000
14.750 1.7466 0.07233 0.06635 -0.1295 0.1389 1.0000
15.000 1.7382 0.07639 0.07048 -0.1288 0.1361 1.0000
15.250 1.7328 0.08013 0.07430 -0.1284 0.1335 1.0000
15.500 1.7330 0.08318 0.07745 -0.1280 0.1309 1.0000
15.750 1.7286 0.08686 0.08120 -0.1277 0.1267 1.0000
16.000 1.7176 0.09139 0.08579 -0.1275 0.1220 1.0000
16.250 1.7107 0.09544 0.08991 -0.1274 0.1167 1.0000
16.500 1.6974 0.10041 0.09489 -0.1274 0.1070 1.0000
16.750 1.6681 0.10767 0.10208 -0.1278 0.0872 1.0000
17.000 1.6372 0.11523 0.10956 -0.1285 0.0706 1.0000
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