GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 500,000 Max Cl/Cd: 99.22 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe222-il-500000.txt Download as CSV file: xf-goe222-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.3324 0.06863 0.06541 -0.1476 0.9712 0.0312
-14.000 -0.3593 0.06050 0.05708 -0.1554 0.9668 0.0312
-13.750 -0.3813 0.05457 0.05096 -0.1606 0.9589 0.0312
-13.250 -0.4126 0.04465 0.04070 -0.1684 0.9429 0.0316
-13.000 -0.4090 0.04208 0.03806 -0.1697 0.9369 0.0319
-12.750 -0.4039 0.04001 0.03596 -0.1707 0.9282 0.0323
-12.500 -0.3930 0.03826 0.03416 -0.1718 0.9220 0.0327
-12.250 -0.3880 0.03613 0.03197 -0.1733 0.9116 0.0330
-12.000 -0.3808 0.03371 0.02941 -0.1764 0.9024 0.0334
-11.750 -0.3659 0.03109 0.02661 -0.1811 0.8920 0.0339
-11.500 -0.3485 0.02909 0.02441 -0.1841 0.8816 0.0344
-11.250 -0.3283 0.02740 0.02250 -0.1861 0.8730 0.0349
-11.000 -0.3077 0.02607 0.02097 -0.1876 0.8616 0.0355
-10.750 -0.2839 0.02510 0.01974 -0.1892 0.8520 0.0360
-10.500 -0.2626 0.02343 0.01794 -0.1897 0.8428 0.0367
-10.250 -0.2392 0.02237 0.01685 -0.1899 0.8343 0.0373
-10.000 -0.2143 0.02154 0.01594 -0.1904 0.8264 0.0378
-9.750 -0.1887 0.02079 0.01511 -0.1910 0.8194 0.0384
-9.500 -0.1628 0.02008 0.01433 -0.1915 0.8126 0.0391
-9.000 -0.1092 0.01887 0.01291 -0.1928 0.8014 0.0407
-8.750 -0.0817 0.01834 0.01227 -0.1933 0.7960 0.0413
-8.500 -0.0535 0.01791 0.01170 -0.1940 0.7912 0.0417
-8.250 -0.0286 0.01688 0.01070 -0.1943 0.7863 0.0425
-8.000 -0.0015 0.01625 0.01005 -0.1949 0.7814 0.0433
-7.750 0.0269 0.01576 0.00951 -0.1956 0.7772 0.0443
-7.500 0.0563 0.01535 0.00902 -0.1965 0.7732 0.0454
-7.250 0.0847 0.01493 0.00857 -0.1971 0.7692 0.0464
-7.000 0.1136 0.01454 0.00813 -0.1978 0.7651 0.0473
-6.750 0.1431 0.01422 0.00773 -0.1984 0.7613 0.0480
-6.500 0.1734 0.01356 0.00700 -0.1998 0.7578 0.0496
-6.250 0.2036 0.01317 0.00656 -0.2007 0.7543 0.0511
-6.000 0.2330 0.01284 0.00620 -0.2014 0.7507 0.0530
-5.750 0.2627 0.01258 0.00588 -0.2020 0.7468 0.0548
-5.500 0.2931 0.01218 0.00542 -0.2029 0.7431 0.0579
-5.250 0.3240 0.01193 0.00508 -0.2038 0.7397 0.0618
-4.750 0.3859 0.01056 0.00423 -0.2067 0.7340 0.1941
-4.500 0.4159 0.01036 0.00420 -0.2074 0.7311 0.2523
-4.250 0.4456 0.01037 0.00421 -0.2078 0.7282 0.2725
-4.000 0.4754 0.01041 0.00423 -0.2082 0.7253 0.2855
-3.750 0.5058 0.01049 0.00425 -0.2087 0.7224 0.2949
-3.500 0.5357 0.01059 0.00432 -0.2091 0.7195 0.3037
-3.250 0.5643 0.01062 0.00434 -0.2093 0.7164 0.3111
-3.000 0.5932 0.01067 0.00440 -0.2095 0.7130 0.3183
-2.750 0.6224 0.01074 0.00440 -0.2097 0.7094 0.3240
-2.500 0.6519 0.01077 0.00441 -0.2101 0.7059 0.3299
-2.250 0.6821 0.01093 0.00452 -0.2105 0.7023 0.3367
-2.000 0.7099 0.01103 0.00461 -0.2105 0.6990 0.3435
-1.750 0.7380 0.01099 0.00462 -0.2106 0.6951 0.3495
-1.500 0.7667 0.01101 0.00462 -0.2108 0.6911 0.3532
-1.250 0.7958 0.01106 0.00463 -0.2110 0.6873 0.3578
-1.000 0.8249 0.01117 0.00467 -0.2113 0.6833 0.3619
-0.750 0.8519 0.01107 0.00463 -0.2112 0.6788 0.3661
-0.500 0.8795 0.01105 0.00462 -0.2112 0.6739 0.3694
-0.250 0.9077 0.01106 0.00460 -0.2113 0.6690 0.3729
0.000 0.9346 0.01107 0.00461 -0.2111 0.6632 0.3765
0.250 0.9606 0.01107 0.00459 -0.2108 0.6563 0.3799
0.500 0.9876 0.01105 0.00453 -0.2107 0.6497 0.3839
0.750 1.0126 0.01101 0.00456 -0.2101 0.6414 0.3876
1.000 1.0377 0.01104 0.00454 -0.2096 0.6327 0.3913
1.250 1.0617 0.01106 0.00457 -0.2089 0.6211 0.3951
1.500 1.0849 0.01113 0.00460 -0.2080 0.6080 0.3987
1.750 1.1066 0.01119 0.00463 -0.2068 0.5924 0.4027
2.000 1.1261 0.01135 0.00473 -0.2053 0.5739 0.4069
2.250 1.1434 0.01162 0.00490 -0.2033 0.5549 0.4112
2.500 1.1584 0.01193 0.00510 -0.2008 0.5379 0.4153
2.750 1.1737 0.01225 0.00534 -0.1985 0.5238 0.4190
3.000 1.1916 0.01257 0.00562 -0.1968 0.5119 0.4237
3.250 1.2110 0.01292 0.00592 -0.1954 0.5015 0.4285
3.500 1.2321 0.01323 0.00621 -0.1943 0.4932 0.4336
3.750 1.2527 0.01356 0.00650 -0.1932 0.4855 0.4388
4.000 1.2738 0.01387 0.00682 -0.1922 0.4791 0.4449
4.250 1.2960 0.01415 0.00711 -0.1914 0.4731 0.4516
4.500 1.3166 0.01449 0.00744 -0.1903 0.4672 0.4580
4.750 1.3378 0.01482 0.00779 -0.1894 0.4622 0.4652
5.000 1.3604 0.01508 0.00809 -0.1887 0.4578 0.4733
5.250 1.3818 0.01538 0.00844 -0.1879 0.4531 0.4820
5.500 1.4016 0.01579 0.00883 -0.1867 0.4482 0.4924
5.750 1.4231 0.01610 0.00921 -0.1859 0.4441 0.5044
6.000 1.4450 0.01639 0.00958 -0.1852 0.4402 0.5181
6.250 1.4661 0.01672 0.00997 -0.1843 0.4363 0.5336
6.500 1.4863 0.01712 0.01040 -0.1833 0.4325 0.5510
6.750 1.5066 0.01754 0.01085 -0.1824 0.4287 0.5702
7.000 1.5277 0.01784 0.01128 -0.1816 0.4254 0.5920
7.250 1.5482 0.01818 0.01173 -0.1807 0.4214 0.6167
7.500 1.5679 0.01857 0.01222 -0.1798 0.4173 0.6469
7.750 1.5871 0.01896 0.01279 -0.1788 0.4131 0.7146
8.000 1.5996 0.01900 0.01321 -0.1762 0.4098 1.0000
8.250 1.6189 0.01945 0.01371 -0.1752 0.4061 1.0000
8.500 1.6370 0.01997 0.01426 -0.1741 0.4019 1.0000
8.750 1.6533 0.02059 0.01487 -0.1727 0.3975 1.0000
9.000 1.6695 0.02123 0.01551 -0.1713 0.3925 1.0000
9.250 1.6853 0.02187 0.01622 -0.1700 0.3864 1.0000
9.500 1.6970 0.02275 0.01707 -0.1681 0.3790 1.0000
9.750 1.7109 0.02355 0.01792 -0.1665 0.3712 1.0000
10.000 1.7212 0.02457 0.01893 -0.1646 0.3621 1.0000
10.250 1.7339 0.02551 0.01991 -0.1631 0.3526 1.0000
10.500 1.7423 0.02676 0.02114 -0.1611 0.3418 1.0000
10.750 1.7498 0.02814 0.02249 -0.1591 0.3280 1.0000
11.000 1.7551 0.02974 0.02405 -0.1570 0.3118 1.0000
11.250 1.7573 0.03163 0.02588 -0.1547 0.2932 1.0000
11.500 1.7564 0.03383 0.02799 -0.1522 0.2753 1.0000
11.750 1.7559 0.03605 0.03016 -0.1498 0.2619 1.0000
12.000 1.7571 0.03819 0.03226 -0.1477 0.2516 1.0000
12.250 1.7618 0.04007 0.03414 -0.1460 0.2439 1.0000
12.500 1.7637 0.04223 0.03629 -0.1442 0.2367 1.0000
12.750 1.7686 0.04414 0.03822 -0.1426 0.2307 1.0000
13.000 1.7739 0.04604 0.04015 -0.1412 0.2253 1.0000
13.250 1.7755 0.04831 0.04242 -0.1395 0.2201 1.0000
13.500 1.7823 0.05012 0.04428 -0.1383 0.2157 1.0000
13.750 1.7890 0.05196 0.04618 -0.1371 0.2114 1.0000
14.000 1.7922 0.05415 0.04838 -0.1358 0.2073 1.0000
14.250 1.7921 0.05668 0.05093 -0.1343 0.2027 1.0000
14.500 1.8014 0.05834 0.05268 -0.1334 0.1988 1.0000
14.750 1.8059 0.06048 0.05487 -0.1324 0.1940 1.0000
15.000 1.8041 0.06332 0.05772 -0.1311 0.1888 1.0000
15.250 1.8103 0.06536 0.05983 -0.1302 0.1836 1.0000
15.500 1.8115 0.06796 0.06247 -0.1292 0.1775 1.0000
15.750 1.8096 0.07091 0.06546 -0.1282 0.1718 1.0000
16.000 1.8117 0.07348 0.06808 -0.1274 0.1640 1.0000
16.250 1.8067 0.07693 0.07153 -0.1265 0.1553 1.0000
16.500 1.7976 0.08091 0.07550 -0.1256 0.1439 1.0000
16.750 1.7832 0.08558 0.08014 -0.1247 0.1300 1.0000
17.000 1.7642 0.09090 0.08542 -0.1240 0.1157 1.0000
17.250 1.7427 0.09666 0.09114 -0.1235 0.1008 1.0000
17.500 1.7144 0.10341 0.09780 -0.1232 0.0776 1.0000
17.750 1.6839 0.11058 0.10488 -0.1234 0.0586 1.0000
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