GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 100,000 Max Cl/Cd: 49.01 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe241-il-100000-n5.txt Download as CSV file: xf-goe241-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.1250 0.11084 0.10544 -0.1109 0.8798 0.0792
-10.500 0.1322 0.10821 0.10279 -0.1122 0.8722 0.0816
-10.250 0.1137 0.10572 0.10030 -0.1178 0.8642 0.0846
-10.000 0.1357 0.10256 0.09714 -0.1160 0.8570 0.0859
-9.750 0.1548 0.10007 0.09460 -0.1156 0.8511 0.0880
-9.500 0.1639 0.09781 0.09234 -0.1161 0.8430 0.0904
-9.250 0.1674 0.09527 0.08977 -0.1177 0.8356 0.0934
-8.750 0.1602 0.08428 0.07870 -0.1240 0.8211 0.0669
-8.500 0.1746 0.08191 0.07627 -0.1240 0.8147 0.0636
-8.000 0.1469 0.06912 0.06344 -0.1326 0.7985 0.0584
-7.750 0.1520 0.06588 0.06015 -0.1340 0.7926 0.0580
-7.500 0.1496 0.06243 0.05673 -0.1357 0.7829 0.0574
-7.250 0.1437 0.05524 0.04941 -0.1443 0.7756 0.0563
-7.000 0.1526 0.04448 0.03811 -0.1671 0.7661 0.0551
-6.750 0.1856 0.03965 0.03273 -0.1777 0.7585 0.0551
-6.500 0.2250 0.03635 0.02892 -0.1847 0.7533 0.0557
-6.250 0.2536 0.03439 0.02660 -0.1881 0.7437 0.0568
-6.000 0.2911 0.03237 0.02410 -0.1921 0.7370 0.0579
-5.750 0.3236 0.03090 0.02227 -0.1942 0.7291 0.0584
-5.500 0.3534 0.02963 0.02082 -0.1954 0.7206 0.0589
-5.250 0.3859 0.02842 0.01946 -0.1966 0.7143 0.0596
-5.000 0.4114 0.02765 0.01865 -0.1966 0.7045 0.0603
-4.750 0.4430 0.02676 0.01764 -0.1974 0.6977 0.0614
-4.500 0.4700 0.02618 0.01698 -0.1976 0.6883 0.0631
-4.250 0.5007 0.02552 0.01615 -0.1981 0.6804 0.0650
-4.000 0.5286 0.02504 0.01555 -0.1981 0.6713 0.0662
-3.750 0.5556 0.02445 0.01502 -0.1978 0.6628 0.0674
-3.500 0.5826 0.02406 0.01465 -0.1975 0.6543 0.0688
-3.250 0.6101 0.02376 0.01434 -0.1974 0.6456 0.0706
-3.000 0.6396 0.02351 0.01400 -0.1976 0.6380 0.0735
-2.750 0.6679 0.02329 0.01379 -0.1979 0.6292 0.0765
-2.250 0.7306 0.02284 0.01315 -0.1998 0.6134 0.0835
-2.000 0.7650 0.02250 0.01268 -0.2015 0.6061 0.0896
-1.750 0.7970 0.02228 0.01239 -0.2028 0.5983 0.0987
-1.500 0.8308 0.02192 0.01202 -0.2046 0.5907 0.1200
-1.250 0.8681 0.02141 0.01219 -0.2074 0.5847 0.3492
-1.000 0.8929 0.02184 0.01264 -0.2067 0.5775 0.3872
-0.750 0.9200 0.02221 0.01290 -0.2064 0.5715 0.4120
-0.500 0.9481 0.02259 0.01313 -0.2061 0.5667 0.4307
-0.250 0.9698 0.02312 0.01372 -0.2047 0.5601 0.4428
0.000 0.9948 0.02352 0.01405 -0.2040 0.5539 0.4570
0.250 1.0226 0.02386 0.01423 -0.2037 0.5485 0.4713
0.500 1.0442 0.02425 0.01464 -0.2026 0.5415 0.4783
0.750 1.0695 0.02448 0.01480 -0.2022 0.5353 0.4837
1.000 1.0995 0.02461 0.01472 -0.2027 0.5302 0.4900
1.250 1.1239 0.02489 0.01496 -0.2024 0.5242 0.4958
1.500 1.1474 0.02519 0.01525 -0.2018 0.5185 0.5002
1.750 1.1742 0.02541 0.01537 -0.2017 0.5137 0.5061
2.000 1.2022 0.02566 0.01548 -0.2020 0.5090 0.5135
2.250 1.2236 0.02603 0.01588 -0.2011 0.5036 0.5178
2.500 1.2471 0.02633 0.01618 -0.2005 0.4985 0.5228
2.750 1.2740 0.02659 0.01632 -0.2005 0.4942 0.5298
3.000 1.2987 0.02693 0.01660 -0.2003 0.4896 0.5362
3.250 1.3173 0.02735 0.01709 -0.1990 0.4840 0.5410
3.500 1.3395 0.02767 0.01738 -0.1982 0.4784 0.5470
3.750 1.3669 0.02791 0.01747 -0.1983 0.4737 0.5540
4.000 1.3831 0.02841 0.01807 -0.1967 0.4685 0.5588
4.250 1.4015 0.02888 0.01858 -0.1955 0.4636 0.5650
4.500 1.4231 0.02928 0.01893 -0.1948 0.4591 0.5717
4.750 1.4481 0.02955 0.01915 -0.1944 0.4552 0.5771
5.000 1.4616 0.03014 0.01980 -0.1924 0.4507 0.5830
5.250 1.4742 0.03077 0.02049 -0.1904 0.4460 0.5892
5.500 1.4909 0.03128 0.02104 -0.1890 0.4415 0.5944
5.750 1.5127 0.03167 0.02138 -0.1883 0.4374 0.6010
6.000 1.5290 0.03230 0.02203 -0.1869 0.4331 0.6070
6.250 1.5374 0.03320 0.02306 -0.1845 0.4279 0.6122
6.500 1.5507 0.03393 0.02383 -0.1828 0.4230 0.6184
6.750 1.5700 0.03440 0.02425 -0.1819 0.4187 0.6246
7.000 1.5804 0.03530 0.02524 -0.1799 0.4138 0.6301
7.250 1.5851 0.03654 0.02660 -0.1774 0.4080 0.6360
7.500 1.5967 0.03741 0.02750 -0.1757 0.4028 0.6420
7.750 1.6156 0.03787 0.02791 -0.1748 0.3983 0.6485
8.000 1.6109 0.03983 0.03009 -0.1717 0.3916 0.6539
8.250 1.6169 0.04114 0.03147 -0.1697 0.3854 0.6598
8.500 1.6321 0.04182 0.03212 -0.1685 0.3803 0.6670
8.750 1.6232 0.04439 0.03490 -0.1657 0.3725 0.6726
9.000 1.6296 0.04580 0.03636 -0.1640 0.3662 0.6792
9.250 1.6299 0.04782 0.03850 -0.1620 0.3594 0.6860
9.500 1.6269 0.05024 0.04103 -0.1601 0.3518 0.6932
9.750 1.6357 0.05155 0.04236 -0.1588 0.3460 0.7022
10.000 1.6244 0.05500 0.04600 -0.1567 0.3378 0.7100
10.250 1.6320 0.05653 0.04756 -0.1555 0.3321 0.7225
10.500 1.6244 0.05985 0.05105 -0.1540 0.3248 0.7352
10.750 1.6257 0.06219 0.05351 -0.1528 0.3188 0.7583
11.000 1.6283 0.06357 0.05498 -0.1510 0.3143 1.0000
11.250 1.6174 0.06773 0.05928 -0.1499 0.3078 1.0000
11.500 1.6221 0.07000 0.06155 -0.1492 0.3033 1.0000
11.750 1.6374 0.07094 0.06241 -0.1485 0.3001 1.0000
12.000 1.6288 0.07501 0.06661 -0.1477 0.2953 1.0000
12.250 1.6257 0.07844 0.07011 -0.1471 0.2911 1.0000
12.500 1.6322 0.08058 0.07227 -0.1465 0.2880 1.0000
12.750 1.6483 0.08142 0.07306 -0.1460 0.2856 1.0000
13.000 1.6610 0.08272 0.07435 -0.1454 0.2832 1.0000
13.250 1.6376 0.08904 0.08088 -0.1451 0.2788 1.0000
13.500 1.6296 0.09332 0.08528 -0.1449 0.2753 1.0000
13.750 1.6339 0.09585 0.08785 -0.1446 0.2729 1.0000
14.000 1.6458 0.09728 0.08930 -0.1442 0.2711 1.0000
14.250 1.6632 0.09790 0.08991 -0.1437 0.2696 1.0000
14.500 1.6860 0.09775 0.08975 -0.1431 0.2684 1.0000
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Polar data table (+)
Polar graphs
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