GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 50,000 Max Cl/Cd: 37.69 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe309-il-50000-n5.txt Download as CSV file: xf-goe309-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3398 0.10325 0.09703 -0.0235 1.0000 0.0865
-7.750 -0.3450 0.10155 0.09545 -0.0266 1.0000 0.0877
-7.500 -0.3462 0.09962 0.09360 -0.0302 1.0000 0.0882
-7.250 -0.3455 0.09753 0.09155 -0.0331 1.0000 0.0885
-7.000 -0.3356 0.09165 0.08579 -0.0297 1.0000 0.0900
-6.750 -0.3307 0.08819 0.08239 -0.0285 1.0000 0.0919
-6.500 -0.3292 0.08549 0.07977 -0.0278 1.0000 0.0944
-6.250 -0.3303 0.08326 0.07761 -0.0276 1.0000 0.0976
-6.000 -0.3341 0.08211 0.07647 -0.0288 1.0000 0.1012
-5.750 -0.3362 0.08112 0.07541 -0.0299 1.0000 0.1021
-5.500 -0.3381 0.07721 0.07165 -0.0267 1.0000 0.1038
-5.250 -0.3278 0.07363 0.06809 -0.0262 0.9963 0.1077
-5.000 -0.2943 0.06904 0.06331 -0.0324 0.9862 0.1104
-4.750 -0.2520 0.06191 0.05575 -0.0402 0.9763 0.0695
-4.500 -0.2166 0.05741 0.05098 -0.0453 0.9659 0.0695
-4.250 -0.1811 0.05321 0.04646 -0.0496 0.9553 0.0704
-4.000 -0.1455 0.04894 0.04182 -0.0534 0.9450 0.0684
-3.750 -0.1054 0.04505 0.03747 -0.0573 0.9365 0.0708
-3.500 -0.0682 0.04152 0.03332 -0.0600 0.9258 0.0741
-3.250 -0.0343 0.03835 0.02960 -0.0616 0.9149 0.0743
-3.000 0.0004 0.03564 0.02642 -0.0633 0.9049 0.0762
-2.750 0.0344 0.03412 0.02468 -0.0649 0.8950 0.0838
-2.500 0.0668 0.03209 0.02213 -0.0655 0.8835 0.0853
-2.250 0.0998 0.03028 0.01980 -0.0661 0.8726 0.0862
-2.000 0.1344 0.02870 0.01771 -0.0667 0.8625 0.0878
-1.750 0.1686 0.02735 0.01608 -0.0675 0.8528 0.0904
-1.500 0.2010 0.02637 0.01487 -0.0678 0.8411 0.0945
-1.250 0.2354 0.02553 0.01363 -0.0683 0.8300 0.1014
-1.000 0.2671 0.02493 0.01287 -0.0685 0.8190 0.1161
-0.750 0.2983 0.02415 0.01201 -0.0685 0.8090 0.1314
-0.500 0.3240 0.02350 0.01134 -0.0677 0.7968 0.1495
-0.250 0.3485 0.02303 0.01097 -0.0669 0.7846 0.1851
0.000 0.3726 0.02262 0.01080 -0.0661 0.7729 0.2500
0.250 0.3902 0.02109 0.01035 -0.0643 0.7624 0.4777
0.750 0.4874 0.02067 0.00988 -0.0708 0.7390 1.0000
1.000 0.5111 0.02091 0.00992 -0.0699 0.7267 1.0000
1.250 0.5350 0.02115 0.00998 -0.0690 0.7149 1.0000
1.500 0.5593 0.02138 0.01004 -0.0681 0.7039 1.0000
1.750 0.5838 0.02160 0.01011 -0.0672 0.6930 1.0000
2.000 0.6068 0.02192 0.01034 -0.0664 0.6809 1.0000
2.250 0.6302 0.02224 0.01058 -0.0655 0.6693 1.0000
2.500 0.6541 0.02252 0.01080 -0.0647 0.6585 1.0000
2.750 0.6790 0.02273 0.01092 -0.0639 0.6486 1.0000
3.000 0.7017 0.02309 0.01127 -0.0630 0.6365 1.0000
3.250 0.7247 0.02343 0.01161 -0.0621 0.6247 1.0000
3.500 0.7481 0.02371 0.01187 -0.0612 0.6127 1.0000
3.750 0.7714 0.02391 0.01205 -0.0601 0.5999 1.0000
4.000 0.7946 0.02409 0.01223 -0.0590 0.5862 1.0000
4.250 0.8177 0.02426 0.01239 -0.0579 0.5721 1.0000
4.500 0.8408 0.02446 0.01260 -0.0568 0.5583 1.0000
4.750 0.8641 0.02468 0.01283 -0.0557 0.5452 1.0000
5.000 0.8875 0.02494 0.01317 -0.0548 0.5324 1.0000
5.250 0.9098 0.02530 0.01361 -0.0538 0.5191 1.0000
5.500 0.9321 0.02568 0.01408 -0.0528 0.5057 1.0000
5.750 0.9544 0.02608 0.01461 -0.0518 0.4923 1.0000
6.000 0.9765 0.02649 0.01514 -0.0508 0.4787 1.0000
6.250 0.9984 0.02693 0.01570 -0.0498 0.4649 1.0000
6.500 1.0202 0.02740 0.01630 -0.0488 0.4510 1.0000
6.750 1.0416 0.02791 0.01696 -0.0477 0.4370 1.0000
7.000 1.0611 0.02820 0.01735 -0.0462 0.4172 1.0000
7.250 1.0753 0.02853 0.01771 -0.0440 0.3895 1.0000
7.500 1.0910 0.02905 0.01833 -0.0422 0.3672 1.0000
7.750 1.1061 0.02965 0.01903 -0.0404 0.3451 1.0000
8.000 1.1157 0.03031 0.01963 -0.0380 0.3133 1.0000
8.250 1.1268 0.03118 0.02053 -0.0359 0.2872 1.0000
8.500 1.1370 0.03218 0.02162 -0.0339 0.2634 1.0000
8.750 1.1452 0.03336 0.02278 -0.0318 0.2408 1.0000
9.000 1.1487 0.03484 0.02416 -0.0294 0.2147 1.0000
9.250 1.1542 0.03626 0.02568 -0.0272 0.1968 1.0000
9.500 1.1541 0.03820 0.02756 -0.0250 0.1699 1.0000
9.750 1.1568 0.04019 0.02962 -0.0234 0.1391 1.0000
10.500 1.1197 0.05193 0.04048 -0.0205 0.0391 1.0000
10.750 1.1146 0.05557 0.04424 -0.0203 0.0369 1.0000
11.000 1.1102 0.05927 0.04811 -0.0204 0.0356 1.0000
11.250 1.1055 0.06313 0.05218 -0.0207 0.0346 1.0000
11.500 1.0999 0.06725 0.05651 -0.0213 0.0338 1.0000
11.750 1.0932 0.07161 0.06107 -0.0221 0.0331 1.0000
12.000 1.0858 0.07619 0.06584 -0.0231 0.0325 1.0000
12.250 1.0780 0.08093 0.07076 -0.0243 0.0319 1.0000
12.500 1.0699 0.08576 0.07576 -0.0255 0.0314 1.0000
12.750 1.0619 0.09067 0.08081 -0.0269 0.0308 1.0000
13.000 1.0543 0.09556 0.08584 -0.0283 0.0303 1.0000
13.250 1.0474 0.10037 0.09074 -0.0296 0.0297 1.0000
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Polar data table (+)
Polar graphs
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