GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 100,000 Max Cl/Cd: 51.57 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe228-il-100000-n5.txt Download as CSV file: xf-goe228-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0571 0.10365 0.09834 -0.1068 0.9407 0.0513
-11.000 -0.0572 0.09923 0.09392 -0.1088 0.9323 0.0513
-10.750 -0.0570 0.09325 0.08792 -0.1129 0.9270 0.0515
-10.500 -0.0477 0.09014 0.08481 -0.1149 0.9209 0.0524
-10.250 -0.0374 0.08795 0.08262 -0.1158 0.9134 0.0534
-9.750 -0.2273 0.05015 0.04423 -0.1467 0.8814 0.0516
-9.500 -0.2145 0.04593 0.03976 -0.1534 0.8755 0.0523
-9.250 -0.2077 0.04351 0.03715 -0.1552 0.8663 0.0528
-9.000 -0.1873 0.04076 0.03414 -0.1586 0.8607 0.0537
-8.750 -0.1598 0.03822 0.03131 -0.1623 0.8570 0.0552
-8.500 -0.1466 0.03651 0.02934 -0.1627 0.8476 0.0566
-8.000 -0.0869 0.03242 0.02458 -0.1676 0.8390 0.0598
-7.750 -0.0676 0.03149 0.02360 -0.1671 0.8305 0.0610
-7.500 -0.0364 0.03021 0.02217 -0.1685 0.8258 0.0628
-7.250 -0.0024 0.02892 0.02063 -0.1703 0.8220 0.0655
-7.000 0.0180 0.02816 0.01970 -0.1697 0.8128 0.0677
-6.750 0.0489 0.02715 0.01871 -0.1706 0.8078 0.0701
-6.500 0.0793 0.02625 0.01773 -0.1714 0.8024 0.0729
-6.250 0.1035 0.02562 0.01698 -0.1711 0.7939 0.0761
-6.000 0.1362 0.02469 0.01604 -0.1723 0.7887 0.0805
-5.750 0.1623 0.02412 0.01541 -0.1724 0.7807 0.0857
-5.250 0.2265 0.02261 0.01376 -0.1746 0.7679 0.1002
-5.000 0.2513 0.02213 0.01333 -0.1747 0.7579 0.1101
-4.750 0.2861 0.02140 0.01255 -0.1763 0.7518 0.1261
-4.500 0.3121 0.02095 0.01217 -0.1766 0.7415 0.1472
-4.250 0.3460 0.02025 0.01162 -0.1781 0.7345 0.1888
-4.000 0.3724 0.02011 0.01164 -0.1782 0.7240 0.2403
-3.750 0.4050 0.01995 0.01139 -0.1789 0.7164 0.2784
-3.500 0.4303 0.02003 0.01140 -0.1784 0.7051 0.2996
-3.250 0.4603 0.01996 0.01119 -0.1787 0.6963 0.3178
-3.000 0.4883 0.01994 0.01102 -0.1786 0.6858 0.3331
-2.750 0.5161 0.01994 0.01092 -0.1785 0.6754 0.3475
-2.500 0.5458 0.01987 0.01074 -0.1786 0.6662 0.3617
-2.250 0.5723 0.01991 0.01070 -0.1784 0.6551 0.3744
-2.000 0.6018 0.01988 0.01050 -0.1786 0.6455 0.3883
-1.750 0.6285 0.01990 0.01048 -0.1783 0.6350 0.3995
-1.500 0.6560 0.01992 0.01040 -0.1782 0.6251 0.4108
-1.250 0.6841 0.01993 0.01029 -0.1781 0.6157 0.4220
-1.000 0.7104 0.01999 0.01030 -0.1779 0.6059 0.4305
-0.750 0.7389 0.02001 0.01019 -0.1780 0.5973 0.4389
-0.500 0.7648 0.02013 0.01025 -0.1777 0.5879 0.4470
-0.250 0.7928 0.02020 0.01022 -0.1777 0.5798 0.4554
0.000 0.8186 0.02035 0.01032 -0.1775 0.5709 0.4641
0.250 0.8457 0.02048 0.01037 -0.1774 0.5632 0.4731
0.500 0.8716 0.02066 0.01052 -0.1771 0.5554 0.4838
0.750 0.8978 0.02085 0.01068 -0.1769 0.5481 0.4948
1.000 0.9251 0.02104 0.01079 -0.1769 0.5418 0.5062
1.250 0.9498 0.02129 0.01105 -0.1765 0.5342 0.5197
1.500 0.9765 0.02151 0.01120 -0.1763 0.5279 0.5344
1.750 1.0017 0.02178 0.01145 -0.1760 0.5215 0.5497
2.000 1.0262 0.02206 0.01174 -0.1755 0.5148 0.5658
2.250 1.0530 0.02231 0.01190 -0.1754 0.5095 0.5828
2.500 1.0776 0.02262 0.01222 -0.1751 0.5039 0.6002
2.750 1.1014 0.02293 0.01255 -0.1745 0.4982 0.6180
3.000 1.1270 0.02321 0.01280 -0.1743 0.4933 0.6363
3.250 1.1531 0.02349 0.01304 -0.1741 0.4889 0.6545
3.500 1.1748 0.02385 0.01348 -0.1733 0.4834 0.6721
3.750 1.1983 0.02416 0.01381 -0.1727 0.4784 0.6908
4.000 1.2237 0.02442 0.01405 -0.1724 0.4743 0.7109
4.250 1.2464 0.02474 0.01443 -0.1717 0.4699 0.7323
4.500 1.2659 0.02508 0.01489 -0.1705 0.4650 0.7568
4.750 1.2863 0.02531 0.01524 -0.1694 0.4606 0.7923
5.000 1.3041 0.02529 0.01534 -0.1674 0.4569 1.0000
5.250 1.3271 0.02580 0.01581 -0.1671 0.4525 1.0000
5.500 1.3462 0.02638 0.01642 -0.1661 0.4476 1.0000
5.750 1.3679 0.02686 0.01687 -0.1655 0.4430 1.0000
6.000 1.3928 0.02727 0.01719 -0.1653 0.4392 1.0000
6.250 1.4108 0.02786 0.01780 -0.1641 0.4352 1.0000
6.500 1.4260 0.02853 0.01853 -0.1625 0.4309 1.0000
6.750 1.4450 0.02912 0.01915 -0.1615 0.4273 1.0000
7.000 1.4667 0.02965 0.01967 -0.1610 0.4242 1.0000
7.250 1.4922 0.03010 0.02006 -0.1609 0.4215 1.0000
7.500 1.5057 0.03092 0.02097 -0.1592 0.4181 1.0000
7.750 1.5177 0.03181 0.02197 -0.1574 0.4146 1.0000
8.000 1.5328 0.03260 0.02284 -0.1560 0.4114 1.0000
8.250 1.5509 0.03328 0.02355 -0.1550 0.4084 1.0000
8.500 1.5726 0.03383 0.02410 -0.1545 0.4058 1.0000
8.750 1.5945 0.03441 0.02469 -0.1540 0.4034 1.0000
9.000 1.5961 0.03582 0.02629 -0.1511 0.4000 1.0000
9.250 1.6019 0.03710 0.02770 -0.1488 0.3966 1.0000
9.500 1.6128 0.03815 0.02884 -0.1472 0.3933 1.0000
9.750 1.6292 0.03893 0.02967 -0.1461 0.3905 1.0000
10.000 1.6505 0.03948 0.03024 -0.1456 0.3881 1.0000
10.250 1.6581 0.04081 0.03169 -0.1438 0.3854 1.0000
10.500 1.6481 0.04322 0.03433 -0.1404 0.3818 1.0000
10.750 1.6460 0.04532 0.03659 -0.1380 0.3787 1.0000
11.000 1.6509 0.04700 0.03839 -0.1363 0.3759 1.0000
11.250 1.6639 0.04813 0.03961 -0.1352 0.3734 1.0000
11.500 1.6845 0.04871 0.04023 -0.1347 0.3713 1.0000
11.750 1.6836 0.05093 0.04259 -0.1328 0.3686 1.0000
12.000 1.6125 0.05944 0.05148 -0.1274 0.3625 1.0000
12.250 1.6010 0.06298 0.05515 -0.1257 0.3580 1.0000
12.500 1.6264 0.06282 0.05503 -0.1253 0.3555 1.0000
12.750 1.6578 0.06213 0.05437 -0.1252 0.3536 1.0000
13.000 1.4420 0.09187 0.08456 -0.1226 0.3343 1.0000
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Polar data table (+)
Polar graphs
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