MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 50,000 Max Cl/Cd: 37.91 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh32-il-50000-n5.txt Download as CSV file: xf-mh32-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4290 0.09207 0.08524 -0.0324 1.0000 0.0359
-8.250 -0.4277 0.08843 0.08168 -0.0331 1.0000 0.0354
-8.000 -0.4282 0.08492 0.07825 -0.0341 1.0000 0.0349
-7.750 -0.4316 0.08124 0.07467 -0.0355 1.0000 0.0344
-7.500 -0.4333 0.07728 0.07079 -0.0376 1.0000 0.0339
-7.250 -0.4355 0.07292 0.06648 -0.0399 1.0000 0.0334
-7.000 -0.4368 0.06886 0.06244 -0.0414 1.0000 0.0328
-6.750 -0.4386 0.06462 0.05817 -0.0425 1.0000 0.0325
-6.500 -0.4386 0.06060 0.05408 -0.0432 1.0000 0.0320
-6.250 -0.4372 0.05654 0.04988 -0.0436 1.0000 0.0315
-6.000 -0.4335 0.05245 0.04557 -0.0437 1.0000 0.0313
-5.750 -0.4268 0.04853 0.04136 -0.0435 1.0000 0.0311
-5.500 -0.4171 0.04480 0.03728 -0.0430 1.0000 0.0315
-5.250 -0.4044 0.04130 0.03332 -0.0424 1.0000 0.0328
-5.000 -0.3886 0.03809 0.02954 -0.0416 1.0000 0.0346
-4.750 -0.3702 0.03530 0.02613 -0.0406 1.0000 0.0360
-4.500 -0.3515 0.03251 0.02297 -0.0397 1.0000 0.0376
-4.250 -0.3315 0.03023 0.02039 -0.0387 1.0000 0.0394
-4.000 -0.3101 0.02827 0.01813 -0.0375 1.0000 0.0421
-3.750 -0.2877 0.02674 0.01609 -0.0362 1.0000 0.0484
-3.500 -0.2669 0.02527 0.01459 -0.0351 1.0000 0.0563
-3.250 -0.2446 0.02382 0.01297 -0.0338 1.0000 0.0666
-3.000 -0.2219 0.02268 0.01173 -0.0329 1.0000 0.0894
-2.750 -0.1984 0.02138 0.01065 -0.0325 1.0000 0.1379
-2.500 -0.1753 0.01985 0.00992 -0.0325 1.0000 0.2821
-2.250 -0.1572 0.01873 0.00973 -0.0310 1.0000 0.4866
-2.000 -0.1454 0.01796 0.00975 -0.0269 1.0000 0.6867
-1.750 -0.0987 0.01739 0.00929 -0.0292 0.9971 1.0000
-1.500 -0.0580 0.01767 0.00903 -0.0325 0.9878 1.0000
-1.250 -0.0175 0.01798 0.00890 -0.0356 0.9786 1.0000
-1.000 0.0237 0.01829 0.00883 -0.0389 0.9692 1.0000
-0.750 0.0616 0.01855 0.00876 -0.0414 0.9585 1.0000
-0.500 0.0997 0.01880 0.00875 -0.0438 0.9476 1.0000
-0.250 0.1383 0.01905 0.00879 -0.0463 0.9368 1.0000
0.000 0.1782 0.01928 0.00881 -0.0490 0.9262 1.0000
0.250 0.2174 0.01947 0.00886 -0.0514 0.9151 1.0000
0.500 0.2536 0.01965 0.00893 -0.0532 0.9028 1.0000
0.750 0.2896 0.01980 0.00902 -0.0548 0.8904 1.0000
1.000 0.3241 0.01993 0.00908 -0.0561 0.8775 1.0000
1.250 0.3578 0.02004 0.00916 -0.0571 0.8642 1.0000
1.500 0.3906 0.02012 0.00922 -0.0579 0.8504 1.0000
1.750 0.4228 0.02017 0.00930 -0.0584 0.8361 1.0000
2.000 0.4546 0.02019 0.00934 -0.0587 0.8213 1.0000
2.250 0.4862 0.02018 0.00935 -0.0589 0.8061 1.0000
2.500 0.5132 0.02023 0.00944 -0.0583 0.7881 1.0000
2.750 0.5416 0.02024 0.00949 -0.0578 0.7702 1.0000
3.000 0.5713 0.02019 0.00956 -0.0574 0.7528 1.0000
3.250 0.5978 0.02023 0.00967 -0.0566 0.7327 1.0000
3.500 0.6259 0.02022 0.00972 -0.0559 0.7128 1.0000
3.750 0.6522 0.02028 0.00985 -0.0549 0.6907 1.0000
4.000 0.6797 0.02030 0.00998 -0.0540 0.6685 1.0000
4.250 0.7056 0.02041 0.01015 -0.0530 0.6439 1.0000
4.500 0.7308 0.02058 0.01037 -0.0518 0.6177 1.0000
4.750 0.7556 0.02079 0.01063 -0.0506 0.5903 1.0000
5.000 0.7798 0.02107 0.01101 -0.0494 0.5615 1.0000
5.250 0.8028 0.02144 0.01142 -0.0480 0.5310 1.0000
5.500 0.8250 0.02186 0.01189 -0.0467 0.4991 1.0000
5.750 0.8468 0.02234 0.01239 -0.0452 0.4669 1.0000
6.000 0.8676 0.02290 0.01298 -0.0438 0.4334 1.0000
6.250 0.8877 0.02354 0.01362 -0.0423 0.3996 1.0000
6.500 0.9069 0.02426 0.01436 -0.0408 0.3651 1.0000
6.750 0.9251 0.02507 0.01526 -0.0392 0.3307 1.0000
7.000 0.9425 0.02598 0.01618 -0.0377 0.2962 1.0000
7.250 0.9588 0.02700 0.01718 -0.0360 0.2626 1.0000
7.500 0.9743 0.02815 0.01833 -0.0344 0.2297 1.0000
7.750 0.9885 0.02942 0.01959 -0.0328 0.1973 1.0000
8.000 1.0010 0.03084 0.02096 -0.0311 0.1675 1.0000
8.250 1.0126 0.03244 0.02252 -0.0293 0.1403 1.0000
8.500 1.0233 0.03420 0.02428 -0.0275 0.1156 1.0000
8.750 1.0335 0.03613 0.02625 -0.0257 0.0956 1.0000
9.000 1.0425 0.03816 0.02833 -0.0239 0.0797 1.0000
9.250 1.0544 0.04060 0.03102 -0.0220 0.0691 1.0000
9.500 1.0623 0.04289 0.03341 -0.0202 0.0596 1.0000
9.750 1.0665 0.04507 0.03566 -0.0182 0.0520 1.0000
10.000 1.0790 0.04828 0.03925 -0.0166 0.0466 1.0000
10.250 1.0815 0.05082 0.04197 -0.0148 0.0419 1.0000
10.500 1.0818 0.05377 0.04502 -0.0132 0.0384 1.0000
10.750 1.0795 0.05733 0.04905 -0.0116 0.0356 1.0000
11.000 1.0750 0.06121 0.05328 -0.0105 0.0344 1.0000
11.250 1.0664 0.06536 0.05773 -0.0099 0.0334 1.0000
11.500 1.0546 0.06986 0.06251 -0.0101 0.0329 1.0000
11.750 1.0400 0.07487 0.06777 -0.0112 0.0325 1.0000
12.000 1.0227 0.08072 0.07387 -0.0135 0.0326 1.0000
12.250 1.0032 0.08749 0.08084 -0.0171 0.0331 1.0000
12.500 0.9811 0.09552 0.08906 -0.0220 0.0339 1.0000
12.750 0.9592 0.10454 0.09822 -0.0279 0.0348 1.0000
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Polar data table (+)
Polar graphs
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