MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 50,000 Max Cl/Cd: 37.79 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh38-il-50000-n5.txt Download as CSV file: xf-mh38-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3531 0.12864 0.12156 -0.0293 1.0000 0.0809
-10.500 -0.3532 0.12614 0.11913 -0.0314 1.0000 0.0828
-10.000 -0.3550 0.11577 0.10891 -0.0383 1.0000 0.0453
-9.250 -0.3426 0.10481 0.09808 -0.0412 1.0000 0.0449
-9.000 -0.3391 0.10124 0.09459 -0.0419 1.0000 0.0446
-8.750 -0.3355 0.09788 0.09131 -0.0422 1.0000 0.0441
-8.500 -0.3338 0.09464 0.08816 -0.0426 1.0000 0.0435
-8.250 -0.3352 0.09144 0.08507 -0.0431 1.0000 0.0430
-8.000 -0.3392 0.08856 0.08232 -0.0431 1.0000 0.0426
-7.750 -0.3474 0.08605 0.07997 -0.0425 1.0000 0.0422
-7.500 -0.3602 0.08401 0.07810 -0.0411 1.0000 0.0419
-7.250 -0.3741 0.08196 0.07620 -0.0397 1.0000 0.0416
-7.000 -0.3885 0.08003 0.07440 -0.0383 1.0000 0.0413
-6.750 -0.4018 0.07772 0.07217 -0.0376 1.0000 0.0409
-6.500 -0.3894 0.07192 0.06635 -0.0447 0.9917 0.0405
-6.250 -0.3667 0.06445 0.05874 -0.0547 0.9814 0.0402
-6.000 -0.3447 0.05683 0.05084 -0.0636 0.9709 0.0402
-5.750 -0.3201 0.04959 0.04313 -0.0713 0.9615 0.0413
-5.500 -0.2877 0.04217 0.03472 -0.0788 0.9545 0.0446
-5.250 -0.2617 0.03933 0.03165 -0.0810 0.9462 0.0494
-5.000 -0.2260 0.03509 0.02664 -0.0845 0.9409 0.0538
-4.750 -0.1974 0.03268 0.02375 -0.0859 0.9331 0.0631
-4.500 -0.1608 0.03018 0.02069 -0.0881 0.9281 0.0740
-4.250 -0.1315 0.02887 0.01911 -0.0889 0.9207 0.0889
-4.000 -0.0962 0.02741 0.01727 -0.0904 0.9155 0.1060
-3.750 -0.0659 0.02649 0.01616 -0.0912 0.9086 0.1282
-3.500 -0.0327 0.02559 0.01506 -0.0923 0.9027 0.1528
-3.250 -0.0026 0.02496 0.01436 -0.0930 0.8961 0.1819
-3.000 0.0285 0.02437 0.01373 -0.0939 0.8896 0.2151
-2.750 0.0597 0.02384 0.01318 -0.0947 0.8836 0.2546
-2.250 0.1189 0.02288 0.01243 -0.0958 0.8708 0.3717
-2.000 0.1434 0.02250 0.01233 -0.0953 0.8633 0.4561
-1.750 0.1701 0.02197 0.01220 -0.0946 0.8579 0.5749
-1.500 0.1866 0.02159 0.01226 -0.0916 0.8500 0.7138
-1.250 0.2356 0.02105 0.01177 -0.0946 0.8460 1.0000
-1.000 0.2597 0.02137 0.01176 -0.0944 0.8376 1.0000
-0.750 0.2929 0.02153 0.01161 -0.0955 0.8322 1.0000
-0.500 0.3157 0.02189 0.01174 -0.0950 0.8236 1.0000
-0.250 0.3484 0.02206 0.01164 -0.0959 0.8183 1.0000
0.000 0.3703 0.02247 0.01189 -0.0953 0.8095 1.0000
0.250 0.4029 0.02264 0.01187 -0.0960 0.8044 1.0000
0.500 0.4240 0.02309 0.01220 -0.0953 0.7953 1.0000
0.750 0.4542 0.02331 0.01228 -0.0957 0.7896 1.0000
1.250 0.5042 0.02405 0.01285 -0.0951 0.7743 1.0000
1.750 0.5541 0.02482 0.01353 -0.0944 0.7588 1.0000
2.000 0.5818 0.02510 0.01377 -0.0944 0.7519 1.0000
2.250 0.6042 0.02558 0.01425 -0.0937 0.7431 1.0000
2.500 0.6343 0.02576 0.01442 -0.0938 0.7371 1.0000
2.750 0.6549 0.02632 0.01505 -0.0930 0.7274 1.0000
3.000 0.6830 0.02657 0.01533 -0.0928 0.7205 1.0000
3.250 0.7066 0.02700 0.01581 -0.0922 0.7116 1.0000
3.500 0.7289 0.02749 0.01637 -0.0915 0.7023 1.0000
3.750 0.7598 0.02755 0.01656 -0.0915 0.6958 1.0000
4.000 0.7798 0.02814 0.01724 -0.0905 0.6851 1.0000
4.250 0.8026 0.02858 0.01780 -0.0897 0.6753 1.0000
4.500 0.8343 0.02853 0.01786 -0.0896 0.6683 1.0000
4.750 0.8545 0.02906 0.01854 -0.0885 0.6568 1.0000
5.000 0.8763 0.02949 0.01920 -0.0875 0.6456 1.0000
5.250 0.9000 0.02980 0.01967 -0.0866 0.6346 1.0000
5.500 0.9267 0.02988 0.01994 -0.0859 0.6243 1.0000
5.750 0.9556 0.02979 0.02004 -0.0852 0.6140 1.0000
6.000 0.9782 0.03003 0.02050 -0.0840 0.6010 1.0000
6.250 1.0017 0.03018 0.02097 -0.0828 0.5876 1.0000
6.500 1.0261 0.03021 0.02124 -0.0816 0.5735 1.0000
6.750 1.0473 0.03038 0.02166 -0.0801 0.5574 1.0000
7.000 1.0668 0.03059 0.02213 -0.0783 0.5392 1.0000
7.250 1.0919 0.03028 0.02207 -0.0767 0.5200 1.0000
7.500 1.1097 0.03032 0.02235 -0.0744 0.4955 1.0000
7.750 1.1289 0.02998 0.02215 -0.0718 0.4638 1.0000
8.000 1.1391 0.03014 0.02234 -0.0684 0.4200 1.0000
8.250 1.1441 0.03072 0.02274 -0.0647 0.3640 1.0000
8.500 1.1424 0.03198 0.02381 -0.0608 0.3045 1.0000
8.750 1.1359 0.03396 0.02541 -0.0572 0.2451 1.0000
9.000 1.1268 0.03660 0.02765 -0.0543 0.1877 1.0000
9.250 1.1152 0.03987 0.03046 -0.0520 0.1368 1.0000
9.500 1.1056 0.04335 0.03359 -0.0502 0.1031 1.0000
9.750 1.0991 0.04679 0.03684 -0.0486 0.0825 1.0000
10.000 1.0950 0.05012 0.04007 -0.0474 0.0677 1.0000
10.250 1.0935 0.05328 0.04323 -0.0464 0.0577 1.0000
10.500 1.0921 0.05652 0.04645 -0.0453 0.0519 1.0000
10.750 1.0974 0.05924 0.04937 -0.0441 0.0448 1.0000
11.000 1.0991 0.06229 0.05235 -0.0434 0.0399 1.0000
11.250 1.1140 0.06444 0.05488 -0.0416 0.0355 1.0000
11.500 1.1316 0.06668 0.05736 -0.0399 0.0324 1.0000
11.750 1.1431 0.06954 0.06029 -0.0389 0.0297 1.0000
12.000 1.1506 0.07305 0.06414 -0.0381 0.0278 1.0000
12.250 1.1516 0.07698 0.06846 -0.0380 0.0264 1.0000
12.500 1.1482 0.08140 0.07323 -0.0382 0.0254 1.0000
12.750 1.1419 0.08623 0.07838 -0.0389 0.0249 1.0000
13.000 1.1322 0.09159 0.08404 -0.0403 0.0247 1.0000
13.250 1.1194 0.09751 0.09023 -0.0423 0.0246 1.0000
13.500 1.1051 0.10386 0.09684 -0.0451 0.0247 1.0000
13.750 1.0893 0.11086 0.10406 -0.0486 0.0248 1.0000
14.000 1.0725 0.11863 0.11203 -0.0531 0.0250 1.0000
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Polar data table (+)
Polar graphs
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