GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 200,000 Max Cl/Cd: 68.14 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe241-il-200000.txt Download as CSV file: xf-goe241-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 241 (MVA PR.1) 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.1380 0.10540 0.10158 -0.1159 0.9069 0.0635
-10.500 0.1441 0.10272 0.09886 -0.1171 0.9009 0.0658
-10.250 0.1249 0.09865 0.09481 -0.1229 0.8908 0.0682
-10.000 0.1442 0.09632 0.09246 -0.1210 0.8853 0.0688
-9.750 0.1589 0.09430 0.09041 -0.1202 0.8783 0.0698
-9.500 0.1699 0.09215 0.08824 -0.1202 0.8707 0.0712
-9.250 0.1778 0.08965 0.08569 -0.1209 0.8648 0.0733
-9.000 0.1548 0.08441 0.08049 -0.1289 0.8545 0.0772
-8.750 0.1758 0.08262 0.07865 -0.1264 0.8487 0.0779
-8.500 0.1919 0.08102 0.07703 -0.1253 0.8413 0.0791
-8.250 0.2045 0.07917 0.07515 -0.1252 0.8336 0.0813
-8.000 0.1790 0.07286 0.06885 -0.1350 0.8251 0.0875
-7.750 0.2028 0.07201 0.06799 -0.1315 0.8178 0.0885
-7.500 0.2213 0.07069 0.06661 -0.1302 0.8114 0.0901
-7.250 0.1951 0.06262 0.05859 -0.1453 0.8014 0.0991
-7.000 0.2160 0.06268 0.05861 -0.1398 0.7946 0.0999
-6.750 0.2359 0.06204 0.05792 -0.1370 0.7880 0.1013
-6.500 0.2512 0.06080 0.05668 -0.1363 0.7790 0.1039
-6.250 0.2667 0.04545 0.04106 -0.1738 0.7715 0.1270
-6.000 0.2776 0.04667 0.04244 -0.1644 0.7625 0.1279
-5.750 0.2956 0.04813 0.04390 -0.1570 0.7550 0.1292
-5.500 0.4009 0.02702 0.02014 -0.2062 0.7480 0.0770
-5.250 0.4291 0.02486 0.01796 -0.2068 0.7392 0.0750
-5.000 0.4627 0.02334 0.01618 -0.2082 0.7324 0.0737
-4.750 0.4921 0.02226 0.01496 -0.2087 0.7221 0.0732
-4.500 0.5250 0.02139 0.01383 -0.2096 0.7147 0.0741
-4.250 0.5536 0.02068 0.01302 -0.2098 0.7037 0.0748
-4.000 0.5854 0.01994 0.01207 -0.2103 0.6957 0.0751
-3.750 0.6132 0.01939 0.01147 -0.2102 0.6842 0.0757
-3.500 0.6437 0.01893 0.01084 -0.2105 0.6753 0.0765
-3.250 0.6715 0.01829 0.01024 -0.2105 0.6646 0.0779
-3.000 0.7012 0.01784 0.00979 -0.2109 0.6555 0.0808
-2.750 0.7303 0.01756 0.00949 -0.2111 0.6453 0.0837
-2.500 0.7605 0.01736 0.00921 -0.2115 0.6364 0.0862
-2.250 0.7914 0.01703 0.00889 -0.2123 0.6268 0.0897
-2.000 0.8229 0.01687 0.00864 -0.2132 0.6181 0.0953
-1.750 0.8541 0.01667 0.00836 -0.2141 0.6087 0.1042
-1.500 0.8866 0.01646 0.00807 -0.2152 0.6005 0.1244
-1.250 0.9195 0.01602 0.00837 -0.2169 0.5914 0.3819
-1.000 0.9469 0.01651 0.00873 -0.2164 0.5842 0.4167
-0.750 0.9718 0.01694 0.00917 -0.2156 0.5762 0.4356
-0.500 0.9988 0.01736 0.00946 -0.2151 0.5696 0.4508
-0.250 1.0239 0.01779 0.00993 -0.2143 0.5634 0.4600
0.000 1.0507 0.01811 0.01016 -0.2140 0.5569 0.4720
0.250 1.0761 0.01848 0.01053 -0.2132 0.5514 0.4789
0.500 1.1035 0.01886 0.01081 -0.2131 0.5460 0.4897
0.750 1.1273 0.01917 0.01118 -0.2121 0.5399 0.4969
1.000 1.1533 0.01946 0.01143 -0.2117 0.5346 0.5046
1.250 1.1845 0.01969 0.01145 -0.2125 0.5302 0.5125
1.500 1.2089 0.01990 0.01175 -0.2119 0.5255 0.5167
1.750 1.2346 0.02011 0.01196 -0.2116 0.5206 0.5221
2.000 1.2630 0.02029 0.01203 -0.2119 0.5158 0.5294
2.250 1.2926 0.02054 0.01215 -0.2124 0.5115 0.5343
2.500 1.3155 0.02075 0.01245 -0.2116 0.5067 0.5394
2.750 1.3407 0.02096 0.01264 -0.2113 0.5015 0.5467
3.000 1.3672 0.02114 0.01277 -0.2112 0.4969 0.5526
3.250 1.3967 0.02144 0.01296 -0.2116 0.4927 0.5583
3.500 1.4189 0.02168 0.01327 -0.2109 0.4884 0.5650
3.750 1.4428 0.02189 0.01351 -0.2104 0.4838 0.5707
4.000 1.4676 0.02210 0.01372 -0.2100 0.4795 0.5766
4.250 1.4962 0.02239 0.01389 -0.2104 0.4756 0.5845
4.500 1.5194 0.02267 0.01423 -0.2098 0.4716 0.5898
4.750 1.5402 0.02293 0.01458 -0.2088 0.4671 0.5957
5.000 1.5638 0.02320 0.01482 -0.2083 0.4627 0.6029
5.250 1.5887 0.02340 0.01501 -0.2079 0.4586 0.6086
5.500 1.6140 0.02373 0.01532 -0.2078 0.4544 0.6156
5.750 1.6310 0.02406 0.01574 -0.2062 0.4497 0.6218
6.000 1.6503 0.02431 0.01606 -0.2050 0.4449 0.6274
6.250 1.6734 0.02456 0.01627 -0.2044 0.4403 0.6346
6.500 1.6953 0.02491 0.01662 -0.2037 0.4357 0.6410
6.750 1.7066 0.02528 0.01713 -0.2011 0.4304 0.6468
7.000 1.7201 0.02560 0.01748 -0.1989 0.4252 0.6533
7.250 1.7436 0.02586 0.01766 -0.1984 0.4202 0.6600
7.500 1.7483 0.02643 0.01839 -0.1949 0.4146 0.6661
7.750 1.7578 0.02699 0.01900 -0.1923 0.4084 0.6727
8.000 1.7765 0.02735 0.01931 -0.1912 0.4027 0.6792
8.250 1.7797 0.02818 0.02030 -0.1879 0.3959 0.6858
8.500 1.7868 0.02893 0.02109 -0.1853 0.3887 0.6928
8.750 1.7970 0.02967 0.02183 -0.1831 0.3815 0.7002
9.000 1.7980 0.03082 0.02310 -0.1800 0.3730 0.7073
9.250 1.8068 0.03172 0.02396 -0.1779 0.3653 0.7151
9.500 1.8070 0.03315 0.02551 -0.1750 0.3560 0.7238
9.750 1.8147 0.03425 0.02658 -0.1730 0.3486 0.7341
10.000 1.8166 0.03583 0.02828 -0.1706 0.3399 0.7458
10.250 1.8258 0.03695 0.02935 -0.1690 0.3335 0.7625
10.500 1.8284 0.03858 0.03119 -0.1669 0.3262 0.7933
10.750 1.8315 0.03979 0.03248 -0.1645 0.3206 1.0000
11.000 1.8425 0.04107 0.03368 -0.1633 0.3158 1.0000
11.250 1.8481 0.04281 0.03550 -0.1618 0.3108 1.0000
11.500 1.8568 0.04430 0.03701 -0.1606 0.3066 1.0000
11.750 1.8697 0.04545 0.03809 -0.1595 0.3031 1.0000
12.000 1.8826 0.04665 0.03926 -0.1585 0.2997 1.0000
12.250 1.8881 0.04849 0.04121 -0.1572 0.2964 1.0000
12.500 1.8957 0.05015 0.04294 -0.1560 0.2932 1.0000
12.750 1.9053 0.05162 0.04443 -0.1550 0.2904 1.0000
13.000 1.9202 0.05262 0.04539 -0.1542 0.2877 1.0000
13.250 1.9376 0.05341 0.04611 -0.1535 0.2846 1.0000
13.500 1.9356 0.05598 0.04886 -0.1520 0.2817 1.0000
13.750 1.9369 0.05828 0.05127 -0.1508 0.2785 1.0000
14.000 1.9416 0.06024 0.05327 -0.1498 0.2753 1.0000
14.250 1.9536 0.06145 0.05445 -0.1490 0.2721 1.0000
14.500 1.9713 0.06213 0.05507 -0.1483 0.2689 1.0000
14.750 1.9652 0.06529 0.05842 -0.1471 0.2666 1.0000
15.000 1.9631 0.06810 0.06137 -0.1461 0.2641 1.0000
15.250 1.9644 0.07057 0.06394 -0.1452 0.2615 1.0000
15.500 1.9702 0.07251 0.06594 -0.1445 0.2590 1.0000
15.750 1.9834 0.07357 0.06698 -0.1439 0.2563 1.0000
16.000 2.0036 0.07387 0.06723 -0.1433 0.2533 1.0000
16.250 1.9881 0.07829 0.07189 -0.1424 0.2513 1.0000
16.500 1.9758 0.08250 0.07629 -0.1418 0.2488 1.0000
16.750 1.9691 0.08606 0.07998 -0.1414 0.2461 1.0000
17.000 1.9718 0.08843 0.08243 -0.1410 0.2435 1.0000
17.250 1.9852 0.08940 0.08338 -0.1406 0.2408 1.0000
17.500 2.0070 0.08926 0.08318 -0.1400 0.2376 1.0000
17.750 1.9801 0.09553 0.08973 -0.1401 0.2356 1.0000
18.000 1.9543 0.10188 0.09632 -0.1405 0.2331 1.0000
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Polar data table (+)
Polar graphs
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