GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 50,000 Max Cl/Cd: 38.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe310-il-50000-n5.txt Download as CSV file: xf-goe310-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3357 0.10462 0.09803 -0.0322 1.0000 0.1188
-8.000 -0.3501 0.10370 0.09727 -0.0317 1.0000 0.1195
-7.750 -0.3641 0.10248 0.09620 -0.0311 1.0000 0.1198
-7.500 -0.3735 0.10084 0.09466 -0.0313 1.0000 0.1201
-6.500 -0.3817 0.08466 0.07865 -0.0308 1.0000 0.0784
-6.250 -0.3778 0.08172 0.07574 -0.0273 1.0000 0.0735
-5.750 -0.3813 0.07363 0.06758 -0.0306 1.0000 0.0643
-5.500 -0.3789 0.07091 0.06487 -0.0292 1.0000 0.0635
-5.250 -0.3540 0.06602 0.05979 -0.0342 0.9932 0.0634
-5.000 -0.3217 0.06023 0.05371 -0.0409 0.9842 0.0640
-4.750 -0.2905 0.05504 0.04824 -0.0458 0.9755 0.0638
-4.500 -0.2611 0.05015 0.04303 -0.0496 0.9661 0.0632
-4.250 -0.2316 0.04460 0.03695 -0.0531 0.9568 0.0639
-4.000 -0.1995 0.04060 0.03248 -0.0560 0.9488 0.0663
-3.750 -0.1709 0.03731 0.02872 -0.0574 0.9390 0.0672
-3.500 -0.1396 0.03423 0.02503 -0.0589 0.9305 0.0682
-3.250 -0.1058 0.03186 0.02213 -0.0604 0.9223 0.0701
-3.000 -0.0742 0.03015 0.01994 -0.0613 0.9127 0.0745
-2.750 -0.0345 0.02840 0.01763 -0.0634 0.9061 0.0781
-2.500 -0.0027 0.02740 0.01644 -0.0642 0.8960 0.0811
-2.250 0.0440 0.02637 0.01510 -0.0675 0.8905 0.0866
-2.000 0.0801 0.02567 0.01420 -0.0689 0.8806 0.0939
-1.750 0.1257 0.02503 0.01357 -0.0721 0.8750 0.1147
-1.500 0.1554 0.02491 0.01353 -0.0723 0.8637 0.1547
-1.250 0.1853 0.02501 0.01345 -0.0726 0.8531 0.2015
-1.000 0.2222 0.02488 0.01316 -0.0741 0.8459 0.2367
-0.750 0.2495 0.02480 0.01297 -0.0740 0.8345 0.2523
-0.500 0.2781 0.02472 0.01288 -0.0742 0.8245 0.2734
-0.250 0.3131 0.02449 0.01259 -0.0753 0.8172 0.2934
0.000 0.3376 0.02451 0.01266 -0.0748 0.8062 0.3205
0.250 0.3667 0.02437 0.01256 -0.0750 0.7973 0.3494
0.500 0.3972 0.02415 0.01232 -0.0754 0.7891 0.3679
0.750 0.4226 0.02404 0.01224 -0.0750 0.7794 0.3901
1.000 0.4539 0.02356 0.01192 -0.0754 0.7725 0.4285
1.250 0.5465 0.02224 0.01170 -0.0886 0.7668 1.0000
1.500 0.5756 0.02237 0.01164 -0.0886 0.7584 1.0000
1.750 0.5984 0.02269 0.01184 -0.0876 0.7484 1.0000
2.000 0.6301 0.02273 0.01175 -0.0879 0.7415 1.0000
2.250 0.6500 0.02315 0.01212 -0.0866 0.7309 1.0000
2.500 0.6755 0.02341 0.01233 -0.0860 0.7223 1.0000
2.750 0.7013 0.02364 0.01252 -0.0854 0.7136 1.0000
3.000 0.7229 0.02404 0.01291 -0.0843 0.7039 1.0000
3.250 0.7530 0.02412 0.01299 -0.0842 0.6963 1.0000
3.500 0.7718 0.02460 0.01351 -0.0826 0.6853 1.0000
3.750 0.7951 0.02491 0.01384 -0.0816 0.6753 1.0000
4.000 0.8251 0.02489 0.01383 -0.0813 0.6656 1.0000
4.250 0.8477 0.02499 0.01397 -0.0798 0.6509 1.0000
4.500 0.8713 0.02497 0.01396 -0.0782 0.6348 1.0000
4.750 0.8904 0.02509 0.01411 -0.0760 0.6170 1.0000
5.000 0.9105 0.02521 0.01431 -0.0740 0.6000 1.0000
5.250 0.9309 0.02539 0.01455 -0.0722 0.5843 1.0000
5.500 0.9502 0.02558 0.01482 -0.0702 0.5678 1.0000
5.750 0.9685 0.02573 0.01503 -0.0680 0.5492 1.0000
6.000 0.9871 0.02585 0.01523 -0.0658 0.5301 1.0000
6.250 1.0038 0.02611 0.01558 -0.0635 0.5117 1.0000
6.500 1.0188 0.02651 0.01612 -0.0611 0.4938 1.0000
6.750 1.0345 0.02693 0.01670 -0.0589 0.4768 1.0000
7.000 1.0499 0.02737 0.01734 -0.0566 0.4593 1.0000
7.250 1.0652 0.02782 0.01794 -0.0544 0.4414 1.0000
7.500 1.0795 0.02827 0.01852 -0.0519 0.4217 1.0000
7.750 1.0900 0.02880 0.01915 -0.0490 0.3967 1.0000
8.000 1.1002 0.02938 0.01977 -0.0460 0.3703 1.0000
8.250 1.1097 0.03004 0.02046 -0.0431 0.3446 1.0000
8.500 1.1178 0.03084 0.02133 -0.0399 0.3215 1.0000
8.750 1.1226 0.03181 0.02231 -0.0366 0.2962 1.0000
9.000 1.1236 0.03305 0.02348 -0.0330 0.2666 1.0000
9.250 1.1210 0.03466 0.02496 -0.0295 0.2338 1.0000
9.500 1.1162 0.03664 0.02679 -0.0263 0.2003 1.0000
9.750 1.1093 0.03901 0.02899 -0.0235 0.1615 1.0000
10.000 1.1019 0.04170 0.03146 -0.0212 0.1272 1.0000
10.250 1.0945 0.04463 0.03416 -0.0193 0.1018 1.0000
10.500 1.0882 0.04767 0.03703 -0.0178 0.0875 1.0000
10.750 1.0828 0.05079 0.04009 -0.0166 0.0792 1.0000
11.000 1.0772 0.05405 0.04331 -0.0155 0.0732 1.0000
11.250 1.0706 0.05750 0.04672 -0.0147 0.0683 1.0000
11.500 1.0678 0.06064 0.04997 -0.0136 0.0638 1.0000
11.750 1.0685 0.06344 0.05281 -0.0124 0.0599 1.0000
12.000 1.0761 0.06561 0.05497 -0.0103 0.0554 1.0000
12.250 1.0872 0.06772 0.05730 -0.0087 0.0502 1.0000
12.750 1.1304 0.07144 0.06149 -0.0048 0.0432 1.0000
13.000 1.1369 0.07445 0.06474 -0.0041 0.0409 1.0000
13.250 1.1554 0.07722 0.06749 -0.0031 0.0379 1.0000
13.500 1.1467 0.08123 0.07191 -0.0031 0.0375 1.0000
13.750 1.1360 0.08572 0.07674 -0.0036 0.0370 1.0000
14.000 1.1251 0.09046 0.08178 -0.0044 0.0367 1.0000
14.250 1.1115 0.09566 0.08725 -0.0059 0.0366 1.0000
14.500 1.0964 0.10128 0.09313 -0.0079 0.0365 1.0000
14.750 1.0810 0.10722 0.09929 -0.0104 0.0365 1.0000
15.000 1.0642 0.11377 0.10604 -0.0135 0.0366 1.0000
15.250 1.0476 0.12073 0.11313 -0.0172 0.0368 1.0000
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Polar data table (+)
Polar graphs
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