GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 50,000 Max Cl/Cd: 34.34 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe309-il-50000.txt Download as CSV file: xf-goe309-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3566 0.10629 0.09996 -0.0167 1.0000 0.1353
-8.000 -0.3617 0.10468 0.09845 -0.0192 1.0000 0.1394
-7.750 -0.3737 0.10435 0.09826 -0.0240 1.0000 0.1408
-7.500 -0.3513 0.09745 0.09135 -0.0196 1.0000 0.1491
-7.250 -0.3574 0.09611 0.09011 -0.0231 1.0000 0.1543
-7.000 -0.3501 0.09181 0.08588 -0.0223 1.0000 0.1593
-6.750 -0.3479 0.08928 0.08342 -0.0229 1.0000 0.1671
-6.500 -0.3534 0.08769 0.08193 -0.0253 1.0000 0.1710
-6.250 -0.3450 0.08348 0.07779 -0.0221 1.0000 0.1784
-6.000 -0.3561 0.08406 0.07837 -0.0252 1.0000 0.1847
-5.750 -0.3493 0.07878 0.07326 -0.0203 1.0000 0.1907
-5.500 -0.3582 0.07917 0.07359 -0.0220 1.0000 0.1994
-5.250 -0.3565 0.07461 0.06920 -0.0173 1.0000 0.2050
-5.000 -0.3602 0.07355 0.06810 -0.0177 1.0000 0.2151
-4.750 -0.3597 0.07052 0.06515 -0.0145 1.0000 0.2244
-4.500 -0.3591 0.06810 0.06275 -0.0131 1.0000 0.2360
-4.250 -0.3571 0.06586 0.06052 -0.0119 1.0000 0.2528
-4.000 -0.3536 0.06363 0.05823 -0.0115 1.0000 0.2740
-3.750 -0.3491 0.06146 0.05602 -0.0106 1.0000 0.3010
-3.500 -0.3455 0.05855 0.05316 -0.0086 1.0000 0.3297
-3.250 -0.3431 0.05534 0.05005 -0.0054 1.0000 0.3622
-3.000 -0.3421 0.05244 0.04724 -0.0017 1.0000 0.4093
-2.750 -0.3381 0.04973 0.04456 0.0009 1.0000 0.4602
-2.500 -0.3320 0.04674 0.04165 0.0042 1.0000 0.5011
-2.250 -0.3246 0.04389 0.03888 0.0073 1.0000 0.5426
-2.000 -0.2929 0.04066 0.03560 0.0054 0.9942 0.5842
-1.750 -0.2026 0.03790 0.03221 -0.0129 0.9815 0.5608
-1.500 -0.0386 0.03989 0.03141 -0.0425 0.9634 0.2122
-1.250 0.0188 0.03776 0.02848 -0.0475 0.9519 0.1835
-1.000 0.0708 0.03600 0.02628 -0.0520 0.9405 0.1786
-0.750 0.1200 0.03498 0.02471 -0.0558 0.9279 0.1846
-0.500 0.1629 0.03384 0.02336 -0.0587 0.9149 0.1884
-0.250 0.2076 0.03315 0.02230 -0.0613 0.9021 0.1980
0.000 0.2516 0.03256 0.02163 -0.0641 0.8893 0.2256
0.250 0.2924 0.03182 0.02094 -0.0661 0.8773 0.2730
0.500 0.3725 0.02847 0.01927 -0.0740 0.8702 1.0000
0.750 0.4079 0.02899 0.01933 -0.0754 0.8563 1.0000
1.000 0.4389 0.02956 0.01962 -0.0762 0.8426 1.0000
1.250 0.4677 0.03016 0.02002 -0.0767 0.8290 1.0000
1.500 0.4938 0.03084 0.02054 -0.0767 0.8156 1.0000
1.750 0.5192 0.03154 0.02111 -0.0765 0.8024 1.0000
2.000 0.5438 0.03228 0.02175 -0.0763 0.7896 1.0000
2.250 0.5694 0.03297 0.02237 -0.0760 0.7771 1.0000
2.500 0.5974 0.03355 0.02288 -0.0759 0.7651 1.0000
2.750 0.6331 0.03371 0.02298 -0.0764 0.7540 1.0000
3.000 0.6544 0.03444 0.02368 -0.0753 0.7403 1.0000
3.250 0.6775 0.03501 0.02426 -0.0742 0.7262 1.0000
3.500 0.7026 0.03538 0.02461 -0.0730 0.7118 1.0000
3.750 0.7286 0.03560 0.02483 -0.0718 0.6971 1.0000
4.000 0.7543 0.03578 0.02503 -0.0704 0.6824 1.0000
4.250 0.7797 0.03595 0.02526 -0.0689 0.6677 1.0000
4.500 0.8045 0.03613 0.02548 -0.0674 0.6531 1.0000
4.750 0.8291 0.03633 0.02573 -0.0659 0.6385 1.0000
5.000 0.8540 0.03649 0.02595 -0.0644 0.6238 1.0000
5.250 0.8751 0.03694 0.02652 -0.0627 0.6078 1.0000
5.500 0.8931 0.03768 0.02736 -0.0609 0.5908 1.0000
5.750 0.9153 0.03804 0.02782 -0.0592 0.5741 1.0000
6.000 0.9398 0.03818 0.02806 -0.0576 0.5576 1.0000
6.250 0.9657 0.03826 0.02828 -0.0560 0.5414 1.0000
6.500 0.9929 0.03826 0.02837 -0.0545 0.5254 1.0000
6.750 1.0209 0.03822 0.02841 -0.0531 0.5095 1.0000
7.000 1.0435 0.03881 0.02912 -0.0516 0.4933 1.0000
7.250 1.0596 0.04022 0.03075 -0.0501 0.4776 1.0000
7.500 1.0774 0.04134 0.03202 -0.0486 0.4621 1.0000
7.750 1.1193 0.03762 0.02817 -0.0459 0.4346 1.0000
8.000 1.1384 0.03778 0.02847 -0.0440 0.4152 1.0000
8.250 1.1693 0.03602 0.02663 -0.0420 0.3927 1.0000
8.500 1.1840 0.03636 0.02718 -0.0399 0.3737 1.0000
8.750 1.2025 0.03639 0.02737 -0.0380 0.3565 1.0000
9.000 1.2223 0.03570 0.02671 -0.0358 0.3370 1.0000
9.250 1.2358 0.03599 0.02721 -0.0336 0.3206 1.0000
9.500 1.2420 0.03619 0.02762 -0.0305 0.2993 1.0000
9.750 1.2443 0.03653 0.02809 -0.0271 0.2757 1.0000
10.000 1.2376 0.03750 0.02903 -0.0232 0.2478 1.0000
10.250 1.2279 0.03907 0.03056 -0.0195 0.2219 1.0000
10.500 1.2182 0.04135 0.03283 -0.0168 0.1947 1.0000
10.750 1.2069 0.04443 0.03591 -0.0151 0.1633 1.0000
11.000 1.1947 0.04816 0.03957 -0.0142 0.1309 1.0000
11.250 1.1830 0.05221 0.04346 -0.0137 0.1095 1.0000
11.500 1.1721 0.05637 0.04746 -0.0135 0.0989 1.0000
11.750 1.1623 0.06056 0.05154 -0.0135 0.0925 1.0000
12.000 1.1564 0.06437 0.05535 -0.0132 0.0873 1.0000
12.250 1.1522 0.06800 0.05900 -0.0128 0.0830 1.0000
12.500 1.1485 0.07146 0.06237 -0.0123 0.0795 1.0000
12.750 1.1514 0.07439 0.06548 -0.0114 0.0759 1.0000
13.000 1.1544 0.07730 0.06852 -0.0106 0.0724 1.0000
13.250 1.1605 0.07974 0.07094 -0.0093 0.0691 1.0000
13.500 1.1748 0.08163 0.07294 -0.0070 0.0667 1.0000
13.750 1.1839 0.08470 0.07640 -0.0058 0.0658 1.0000
14.000 1.1845 0.08891 0.08092 -0.0058 0.0654 1.0000
14.250 1.1773 0.09411 0.08642 -0.0068 0.0654 1.0000
14.500 1.1643 0.10018 0.09276 -0.0089 0.0657 1.0000
14.750 1.1476 0.10701 0.09983 -0.0118 0.0661 1.0000
15.000 1.1282 0.11465 0.10766 -0.0156 0.0666 1.0000
15.250 1.1086 0.12284 0.11600 -0.0199 0.0672 1.0000
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Polar data table (+)
Polar graphs
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