MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 100,000 Max Cl/Cd: 61.64 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh38-il-100000-n5.txt Download as CSV file: xf-mh38-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 38 9.68%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3295 0.09191 0.08722 -0.0411 1.0000 0.0200
-8.500 -0.3302 0.08845 0.08385 -0.0421 1.0000 0.0198
-8.250 -0.3336 0.08503 0.08052 -0.0428 1.0000 0.0198
-8.000 -0.3398 0.08214 0.07775 -0.0428 1.0000 0.0195
-7.750 -0.3532 0.08003 0.07580 -0.0413 1.0000 0.0194
-7.500 -0.3480 0.07528 0.07111 -0.0466 0.9849 0.0191
-7.250 -0.3302 0.06779 0.06362 -0.0577 0.9701 0.0190
-7.000 -0.3099 0.05921 0.05496 -0.0705 0.9564 0.0187
-6.750 -0.2908 0.04803 0.04351 -0.0837 0.9427 0.0183
-6.500 -0.2734 0.03874 0.03357 -0.0922 0.9299 0.0182
-6.250 -0.2523 0.03261 0.02666 -0.0959 0.9191 0.0187
-6.000 -0.2267 0.02832 0.02158 -0.0978 0.9108 0.0201
-5.750 -0.2000 0.02560 0.01823 -0.0986 0.9024 0.0233
-5.500 -0.1740 0.02397 0.01638 -0.0990 0.8942 0.0269
-5.250 -0.1456 0.02207 0.01403 -0.0992 0.8872 0.0316
-5.000 -0.1195 0.02098 0.01280 -0.0992 0.8789 0.0397
-4.750 -0.0910 0.01973 0.01133 -0.0994 0.8728 0.0496
-4.500 -0.0649 0.01897 0.01043 -0.0992 0.8644 0.0623
-4.250 -0.0366 0.01832 0.00961 -0.0993 0.8584 0.0783
-4.000 -0.0105 0.01773 0.00891 -0.0990 0.8504 0.0937
-3.750 0.0174 0.01723 0.00833 -0.0990 0.8445 0.1132
-3.500 0.0435 0.01684 0.00790 -0.0988 0.8368 0.1336
-3.250 0.0713 0.01644 0.00747 -0.0987 0.8313 0.1581
-3.000 0.0972 0.01613 0.00716 -0.0985 0.8237 0.1837
-2.750 0.1247 0.01579 0.00679 -0.0984 0.8183 0.2162
-2.500 0.1506 0.01552 0.00659 -0.0981 0.8110 0.2540
-2.250 0.1777 0.01522 0.00636 -0.0980 0.8054 0.3038
-2.000 0.2035 0.01495 0.00626 -0.0977 0.7987 0.3651
-1.750 0.2295 0.01467 0.00614 -0.0973 0.7928 0.4396
-1.500 0.2548 0.01441 0.00607 -0.0967 0.7867 0.5258
-1.250 0.2788 0.01411 0.00605 -0.0956 0.7805 0.6245
-1.000 0.3006 0.01379 0.00602 -0.0937 0.7750 0.7399
-0.750 0.3333 0.01343 0.00590 -0.0937 0.7688 0.9178
-0.500 0.3694 0.01340 0.00567 -0.0953 0.7638 1.0000
-0.250 0.3955 0.01356 0.00570 -0.0952 0.7566 1.0000
0.000 0.4228 0.01366 0.00564 -0.0950 0.7511 1.0000
0.250 0.4491 0.01382 0.00569 -0.0948 0.7443 1.0000
0.500 0.4762 0.01394 0.00569 -0.0946 0.7384 1.0000
0.750 0.5027 0.01410 0.00577 -0.0944 0.7319 1.0000
1.000 0.5295 0.01423 0.00582 -0.0942 0.7256 1.0000
1.250 0.5562 0.01438 0.00592 -0.0940 0.7193 1.0000
1.500 0.5828 0.01454 0.00603 -0.0938 0.7125 1.0000
1.750 0.6097 0.01468 0.00612 -0.0936 0.7064 1.0000
2.000 0.6360 0.01485 0.00628 -0.0933 0.6992 1.0000
2.500 0.6891 0.01517 0.00661 -0.0928 0.6854 1.0000
2.750 0.7157 0.01533 0.00677 -0.0925 0.6784 1.0000
3.000 0.7421 0.01549 0.00695 -0.0922 0.6709 1.0000
3.250 0.7681 0.01567 0.00721 -0.0919 0.6630 1.0000
3.500 0.7950 0.01578 0.00734 -0.0916 0.6556 1.0000
3.750 0.8203 0.01599 0.00763 -0.0912 0.6464 1.0000
4.000 0.8468 0.01612 0.00781 -0.0908 0.6381 1.0000
4.250 0.8729 0.01626 0.00801 -0.0903 0.6289 1.0000
4.500 0.8980 0.01645 0.00836 -0.0898 0.6184 1.0000
4.750 0.9236 0.01661 0.00861 -0.0893 0.6079 1.0000
5.000 0.9493 0.01674 0.00884 -0.0888 0.5972 1.0000
5.250 0.9749 0.01688 0.00906 -0.0882 0.5857 1.0000
5.500 0.9999 0.01703 0.00933 -0.0875 0.5729 1.0000
5.750 1.0242 0.01722 0.00966 -0.0868 0.5581 1.0000
6.000 1.0479 0.01742 0.01008 -0.0859 0.5413 1.0000
6.250 1.0714 0.01761 0.01038 -0.0850 0.5222 1.0000
6.500 1.0938 0.01782 0.01069 -0.0838 0.4985 1.0000
6.750 1.1145 0.01808 0.01098 -0.0824 0.4668 1.0000
7.000 1.1322 0.01852 0.01131 -0.0805 0.4222 1.0000
7.250 1.1462 0.01928 0.01183 -0.0782 0.3644 1.0000
7.500 1.1563 0.02039 0.01262 -0.0757 0.3003 1.0000
7.750 1.1618 0.02189 0.01371 -0.0728 0.2282 1.0000
8.000 1.1630 0.02379 0.01509 -0.0697 0.1521 1.0000
8.250 1.1613 0.02596 0.01681 -0.0664 0.0853 1.0000
8.500 1.1595 0.02795 0.01850 -0.0629 0.0528 1.0000
8.750 1.1600 0.02985 0.02032 -0.0598 0.0370 1.0000
9.000 1.1595 0.03191 0.02240 -0.0569 0.0296 1.0000
9.250 1.1629 0.03374 0.02440 -0.0546 0.0247 1.0000
9.500 1.1645 0.03581 0.02653 -0.0526 0.0206 1.0000
9.750 1.1640 0.03818 0.02903 -0.0505 0.0187 1.0000
10.000 1.1668 0.04041 0.03146 -0.0487 0.0173 1.0000
10.250 1.1707 0.04269 0.03390 -0.0471 0.0163 1.0000
10.500 1.1762 0.04497 0.03633 -0.0457 0.0152 1.0000
10.750 1.1817 0.04725 0.03872 -0.0446 0.0137 1.0000
11.000 1.1859 0.04975 0.04132 -0.0436 0.0126 1.0000
11.250 1.1908 0.05284 0.04452 -0.0424 0.0115 1.0000
11.500 1.1991 0.05532 0.04726 -0.0414 0.0109 1.0000
11.750 1.2062 0.05823 0.05042 -0.0404 0.0106 1.0000
12.000 1.2105 0.06152 0.05399 -0.0396 0.0104 1.0000
12.250 1.2110 0.06515 0.05790 -0.0390 0.0102 1.0000
12.500 1.2078 0.06920 0.06226 -0.0387 0.0100 1.0000
12.750 1.2015 0.07357 0.06699 -0.0389 0.0099 1.0000
13.000 1.1921 0.07837 0.07207 -0.0395 0.0099 1.0000
13.250 1.1802 0.08363 0.07760 -0.0407 0.0098 1.0000
13.500 1.1671 0.08918 0.08341 -0.0424 0.0099 1.0000
13.750 1.1525 0.09525 0.08972 -0.0448 0.0099 1.0000
14.000 1.1366 0.10196 0.09667 -0.0479 0.0099 1.0000
14.250 1.1205 0.10916 0.10407 -0.0518 0.0100 1.0000
14.500 1.1041 0.11698 0.11210 -0.0564 0.0101 1.0000
14.750 1.0874 0.12554 0.12075 -0.0617 0.0102 1.0000
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Polar data table (+)
Polar graphs
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