MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 200,000 Max Cl/Cd: 85.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh38-il-200000-n5.txt Download as CSV file: xf-mh38-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3411 0.08851 0.08514 -0.0402 1.0000 0.0073
-8.750 -0.3422 0.08483 0.08152 -0.0415 1.0000 0.0073
-8.500 -0.3459 0.08100 0.07776 -0.0426 1.0000 0.0073
-8.250 -0.3501 0.07652 0.07338 -0.0448 0.9959 0.0073
-8.000 -0.3393 0.06994 0.06681 -0.0531 0.9667 0.0071
-7.750 -0.3291 0.06129 0.05815 -0.0654 0.9413 0.0070
-7.500 -0.3226 0.04895 0.04572 -0.0815 0.9161 0.0067
-7.250 -0.3260 0.03309 0.02901 -0.0939 0.8947 0.0064
-7.000 -0.3122 0.02773 0.02292 -0.0959 0.8821 0.0065
-6.750 -0.2929 0.02430 0.01886 -0.0964 0.8720 0.0068
-6.500 -0.2709 0.02189 0.01595 -0.0963 0.8622 0.0072
-6.250 -0.2468 0.02031 0.01392 -0.0961 0.8536 0.0078
-6.000 -0.2229 0.01891 0.01229 -0.0961 0.8458 0.0096
-5.750 -0.1972 0.01814 0.01132 -0.0960 0.8375 0.0116
-5.500 -0.1716 0.01697 0.00986 -0.0956 0.8305 0.0132
-5.250 -0.1463 0.01564 0.00832 -0.0954 0.8228 0.0160
-5.000 -0.1196 0.01515 0.00768 -0.0952 0.8163 0.0219
-4.750 -0.0932 0.01437 0.00679 -0.0950 0.8091 0.0303
-4.500 -0.0664 0.01385 0.00618 -0.0949 0.8030 0.0411
-4.250 -0.0394 0.01343 0.00567 -0.0948 0.7961 0.0538
-4.000 -0.0123 0.01307 0.00523 -0.0946 0.7905 0.0670
-3.750 0.0150 0.01278 0.00489 -0.0946 0.7837 0.0828
-3.500 0.0424 0.01251 0.00454 -0.0945 0.7781 0.0973
-3.250 0.0697 0.01226 0.00429 -0.0945 0.7719 0.1155
-3.000 0.0971 0.01204 0.00405 -0.0944 0.7661 0.1358
-2.750 0.1245 0.01183 0.00382 -0.0944 0.7606 0.1587
-2.500 0.1520 0.01163 0.00364 -0.0944 0.7545 0.1840
-2.250 0.1794 0.01144 0.00346 -0.0943 0.7497 0.2155
-2.000 0.2068 0.01125 0.00335 -0.0944 0.7433 0.2524
-1.750 0.2341 0.01106 0.00324 -0.0943 0.7380 0.2972
-1.500 0.2613 0.01086 0.00315 -0.0943 0.7324 0.3516
-1.250 0.2883 0.01066 0.00311 -0.0942 0.7267 0.4141
-1.000 0.3150 0.01046 0.00307 -0.0940 0.7218 0.4834
-0.750 0.3412 0.01024 0.00307 -0.0937 0.7156 0.5597
-0.500 0.3663 0.01000 0.00307 -0.0930 0.7104 0.6477
-0.250 0.3895 0.00973 0.00310 -0.0917 0.7047 0.7489
0.000 0.4135 0.00945 0.00308 -0.0901 0.6991 0.8846
0.250 0.4532 0.00938 0.00296 -0.0925 0.6938 1.0000
0.500 0.4807 0.00946 0.00297 -0.0925 0.6875 1.0000
0.750 0.5082 0.00954 0.00296 -0.0924 0.6822 1.0000
1.000 0.5356 0.00963 0.00301 -0.0924 0.6757 1.0000
1.250 0.5631 0.00973 0.00304 -0.0923 0.6699 1.0000
1.500 0.5904 0.00982 0.00310 -0.0922 0.6636 1.0000
1.750 0.6178 0.00992 0.00315 -0.0921 0.6572 1.0000
2.000 0.6452 0.01002 0.00323 -0.0920 0.6508 1.0000
2.250 0.6724 0.01013 0.00334 -0.0919 0.6439 1.0000
2.500 0.6997 0.01024 0.00344 -0.0918 0.6370 1.0000
2.750 0.7268 0.01034 0.00354 -0.0917 0.6297 1.0000
3.000 0.7539 0.01046 0.00366 -0.0916 0.6219 1.0000
3.250 0.7809 0.01057 0.00379 -0.0914 0.6142 1.0000
3.500 0.8077 0.01069 0.00395 -0.0912 0.6049 1.0000
3.750 0.8345 0.01082 0.00410 -0.0910 0.5960 1.0000
4.000 0.8611 0.01095 0.00423 -0.0908 0.5867 1.0000
4.250 0.8876 0.01109 0.00443 -0.0905 0.5760 1.0000
4.500 0.9139 0.01124 0.00466 -0.0902 0.5649 1.0000
4.750 0.9401 0.01139 0.00486 -0.0899 0.5529 1.0000
5.000 0.9659 0.01156 0.00508 -0.0896 0.5395 1.0000
5.250 0.9914 0.01175 0.00531 -0.0891 0.5242 1.0000
5.500 1.0164 0.01197 0.00554 -0.0886 0.5063 1.0000
5.750 1.0407 0.01222 0.00586 -0.0880 0.4835 1.0000
6.000 1.0634 0.01257 0.00615 -0.0871 0.4530 1.0000
6.250 1.0836 0.01309 0.00650 -0.0858 0.4088 1.0000
6.500 1.1016 0.01380 0.00700 -0.0844 0.3566 1.0000
6.750 1.1186 0.01463 0.00761 -0.0829 0.3050 1.0000
7.000 1.1324 0.01572 0.00839 -0.0810 0.2433 1.0000
7.250 1.1429 0.01708 0.00935 -0.0789 0.1734 1.0000
7.500 1.1505 0.01867 0.01048 -0.0764 0.1031 1.0000
7.750 1.1581 0.02020 0.01167 -0.0740 0.0543 1.0000
8.000 1.1668 0.02157 0.01287 -0.0715 0.0294 1.0000
8.250 1.1754 0.02280 0.01415 -0.0689 0.0181 1.0000
8.500 1.1830 0.02397 0.01539 -0.0662 0.0133 1.0000
8.750 1.1898 0.02523 0.01674 -0.0636 0.0104 1.0000
9.000 1.1983 0.02641 0.01804 -0.0614 0.0086 1.0000
9.250 1.2048 0.02781 0.01956 -0.0591 0.0078 1.0000
9.500 1.2081 0.02954 0.02141 -0.0568 0.0071 1.0000
9.750 1.2076 0.03170 0.02372 -0.0544 0.0066 1.0000
10.000 1.2085 0.03390 0.02605 -0.0524 0.0063 1.0000
10.250 1.2136 0.03584 0.02812 -0.0508 0.0061 1.0000
10.500 1.2184 0.03792 0.03034 -0.0493 0.0060 1.0000
10.750 1.2235 0.04012 0.03269 -0.0479 0.0057 1.0000
11.000 1.2294 0.04235 0.03507 -0.0466 0.0056 1.0000
11.250 1.2356 0.04472 0.03761 -0.0453 0.0054 1.0000
11.500 1.2417 0.04725 0.04032 -0.0441 0.0053 1.0000
11.750 1.2471 0.04992 0.04319 -0.0430 0.0053 1.0000
12.000 1.2508 0.05285 0.04641 -0.0421 0.0052 1.0000
12.250 1.2522 0.05605 0.04984 -0.0413 0.0051 1.0000
12.500 1.2506 0.05967 0.05372 -0.0407 0.0050 1.0000
12.750 1.2466 0.06357 0.05787 -0.0405 0.0050 1.0000
13.000 1.2401 0.06779 0.06235 -0.0406 0.0050 1.0000
13.250 1.2314 0.07236 0.06716 -0.0412 0.0049 1.0000
13.500 1.2217 0.07719 0.07223 -0.0422 0.0048 1.0000
13.750 1.2103 0.08248 0.07774 -0.0437 0.0048 1.0000
14.000 1.1988 0.08801 0.08347 -0.0458 0.0046 1.0000
14.250 1.1837 0.09463 0.09033 -0.0486 0.0047 1.0000
14.500 1.1684 0.10168 0.09760 -0.0520 0.0047 1.0000
14.750 1.1540 0.10893 0.10503 -0.0559 0.0046 1.0000
15.000 1.1345 0.11800 0.11433 -0.0611 0.0048 1.0000
15.250 1.1157 0.12758 0.12410 -0.0670 0.0049 1.0000
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Polar data table (+)
Polar graphs
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