MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 500,000 Max Cl/Cd: 95.88 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh201-il-500000.txt Download as CSV file: xf-mh201-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 201 13.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4542 0.06327 0.06107 -0.0718 0.9938 0.0201
-9.000 -0.4671 0.05506 0.05263 -0.0820 0.9858 0.0202
-8.750 -0.4803 0.04804 0.04477 -0.0902 0.9730 0.0213
-8.500 -0.4780 0.04130 0.03791 -0.0919 0.9659 0.0219
-8.250 -0.4552 0.03861 0.03518 -0.0940 0.9624 0.0224
-8.000 -0.4291 0.03626 0.03271 -0.0965 0.9601 0.0233
-7.750 -0.4082 0.03649 0.03231 -0.0965 0.9522 0.0264
-7.500 -0.3892 0.03037 0.02615 -0.0987 0.9493 0.0278
-7.250 -0.3638 0.02094 0.01547 -0.0978 0.9469 0.0130
-7.000 -0.3302 0.01871 0.01304 -0.0995 0.9455 0.0123
-6.750 -0.3068 0.01716 0.01132 -0.0987 0.9383 0.0120
-6.500 -0.2745 0.01581 0.00983 -0.0998 0.9350 0.0117
-6.250 -0.2405 0.01466 0.00859 -0.1014 0.9322 0.0118
-6.000 -0.2133 0.01383 0.00770 -0.1016 0.9256 0.0119
-5.750 -0.1827 0.01306 0.00686 -0.1025 0.9202 0.0123
-5.500 -0.1492 0.01234 0.00606 -0.1040 0.9160 0.0131
-5.250 -0.1245 0.01173 0.00539 -0.1036 0.9076 0.0139
-5.000 -0.0930 0.01120 0.00481 -0.1046 0.9023 0.0165
-4.750 -0.0673 0.01063 0.00423 -0.1044 0.8947 0.0246
-4.500 -0.0405 0.00973 0.00366 -0.1048 0.8883 0.0961
-4.250 -0.0143 0.00907 0.00337 -0.1052 0.8817 0.1863
-4.000 0.0121 0.00846 0.00312 -0.1055 0.8751 0.2850
-3.750 0.0406 0.00776 0.00287 -0.1064 0.8697 0.4154
-3.500 0.0668 0.00731 0.00273 -0.1065 0.8629 0.5100
-3.250 0.0952 0.00704 0.00270 -0.1067 0.8573 0.5937
-3.000 0.1231 0.00701 0.00277 -0.1066 0.8515 0.6454
-2.750 0.1511 0.00705 0.00279 -0.1064 0.8452 0.6695
-2.500 0.1809 0.00713 0.00279 -0.1067 0.8399 0.6879
-2.250 0.2080 0.00721 0.00285 -0.1064 0.8333 0.7015
-2.000 0.2362 0.00728 0.00288 -0.1062 0.8273 0.7122
-1.750 0.2648 0.00737 0.00290 -0.1063 0.8215 0.7222
-1.500 0.2920 0.00744 0.00296 -0.1060 0.8147 0.7303
-1.250 0.3212 0.00753 0.00296 -0.1061 0.8090 0.7381
-1.000 0.3476 0.00759 0.00303 -0.1057 0.8020 0.7446
-0.750 0.3764 0.00766 0.00302 -0.1058 0.7956 0.7518
-0.500 0.4032 0.00771 0.00308 -0.1054 0.7888 0.7568
-0.250 0.4304 0.00777 0.00312 -0.1051 0.7816 0.7632
0.000 0.4582 0.00784 0.00315 -0.1050 0.7747 0.7696
0.250 0.4844 0.00789 0.00321 -0.1044 0.7667 0.7747
0.500 0.5123 0.00795 0.00322 -0.1044 0.7593 0.7800
0.750 0.5396 0.00797 0.00322 -0.1042 0.7508 0.7843
1.000 0.5662 0.00800 0.00325 -0.1038 0.7425 0.7878
1.250 0.5930 0.00804 0.00327 -0.1035 0.7334 0.7916
1.500 0.6200 0.00808 0.00330 -0.1033 0.7235 0.7958
1.750 0.6474 0.00812 0.00330 -0.1032 0.7136 0.7996
2.000 0.6729 0.00814 0.00333 -0.1026 0.7023 0.8029
2.250 0.6988 0.00819 0.00339 -0.1022 0.6901 0.8067
2.500 0.7250 0.00825 0.00342 -0.1018 0.6762 0.8107
2.750 0.7514 0.00832 0.00345 -0.1015 0.6607 0.8144
3.000 0.7759 0.00838 0.00349 -0.1008 0.6431 0.8171
3.250 0.7999 0.00849 0.00355 -0.0999 0.6227 0.8201
3.500 0.8240 0.00863 0.00363 -0.0992 0.5988 0.8232
3.750 0.8476 0.00884 0.00373 -0.0984 0.5733 0.8265
4.000 0.8709 0.00909 0.00386 -0.0976 0.5460 0.8296
4.250 0.8928 0.00932 0.00401 -0.0965 0.5180 0.8322
4.500 0.9143 0.00959 0.00419 -0.0953 0.4892 0.8351
4.750 0.9359 0.00990 0.00440 -0.0942 0.4600 0.8383
5.000 0.9576 0.01023 0.00462 -0.0932 0.4307 0.8415
5.250 0.9796 0.01059 0.00486 -0.0923 0.4024 0.8447
5.500 0.9996 0.01094 0.00511 -0.0909 0.3748 0.8476
5.750 1.0202 0.01129 0.00538 -0.0897 0.3485 0.8506
6.000 1.0409 0.01167 0.00567 -0.0885 0.3227 0.8540
6.250 1.0614 0.01208 0.00598 -0.0874 0.2987 0.8577
6.500 1.0823 0.01245 0.00628 -0.0864 0.2765 0.8610
6.750 1.1012 0.01285 0.00662 -0.0849 0.2551 0.8643
7.000 1.1207 0.01325 0.00696 -0.0836 0.2353 0.8680
7.250 1.1396 0.01366 0.00731 -0.0822 0.2164 0.8724
7.500 1.1574 0.01406 0.00767 -0.0805 0.1993 0.8765
7.750 1.1739 0.01447 0.00805 -0.0787 0.1840 0.8807
8.000 1.1909 0.01493 0.00847 -0.0770 0.1690 0.8856
8.250 1.2081 0.01539 0.00891 -0.0753 0.1554 0.8908
8.500 1.2235 0.01584 0.00936 -0.0733 0.1433 0.8966
8.750 1.2398 0.01634 0.00985 -0.0716 0.1317 0.9033
9.000 1.2533 0.01685 0.01036 -0.0694 0.1215 0.9105
9.250 1.2683 0.01735 0.01087 -0.0674 0.1125 0.9194
9.500 1.2806 0.01780 0.01138 -0.0650 0.1048 0.9324
9.750 1.2902 0.01830 0.01193 -0.0621 0.0972 0.9680
10.000 1.3099 0.01888 0.01254 -0.0615 0.0902 1.0000
10.250 1.3257 0.01971 0.01334 -0.0603 0.0830 1.0000
10.500 1.3438 0.02037 0.01402 -0.0594 0.0769 1.0000
10.750 1.3572 0.02128 0.01493 -0.0580 0.0710 1.0000
11.000 1.3737 0.02199 0.01569 -0.0569 0.0660 1.0000
11.250 1.3837 0.02312 0.01680 -0.0551 0.0608 1.0000
11.500 1.3999 0.02384 0.01760 -0.0540 0.0571 1.0000
11.750 1.4111 0.02491 0.01867 -0.0525 0.0529 1.0000
12.000 1.4218 0.02603 0.01985 -0.0510 0.0493 1.0000
12.250 1.4341 0.02706 0.02094 -0.0497 0.0458 1.0000
12.500 1.4398 0.02861 0.02249 -0.0479 0.0422 1.0000
12.750 1.4518 0.02972 0.02370 -0.0468 0.0396 1.0000
13.000 1.4614 0.03102 0.02504 -0.0456 0.0369 1.0000
13.250 1.4637 0.03297 0.02702 -0.0439 0.0340 1.0000
13.500 1.4759 0.03414 0.02829 -0.0431 0.0317 1.0000
13.750 1.4826 0.03581 0.02999 -0.0420 0.0293 1.0000
14.000 1.4857 0.03785 0.03208 -0.0409 0.0270 1.0000
14.250 1.4950 0.03938 0.03371 -0.0401 0.0250 1.0000
14.500 1.4985 0.04150 0.03587 -0.0393 0.0232 1.0000
14.750 1.5001 0.04389 0.03834 -0.0386 0.0216 1.0000
15.000 1.5069 0.04581 0.04035 -0.0382 0.0199 1.0000
15.250 1.5080 0.04842 0.04304 -0.0377 0.0187 1.0000
15.500 1.5040 0.05172 0.04641 -0.0375 0.0175 1.0000
15.750 1.5059 0.05447 0.04929 -0.0375 0.0167 1.0000
16.000 1.5066 0.05745 0.05239 -0.0376 0.0157 1.0000
16.250 1.5039 0.06099 0.05603 -0.0381 0.0149 1.0000
16.500 1.4964 0.06536 0.06049 -0.0390 0.0142 1.0000
16.750 1.4901 0.06973 0.06500 -0.0400 0.0136 1.0000
17.000 1.4867 0.07387 0.06929 -0.0413 0.0130 1.0000
17.250 1.4804 0.07858 0.07414 -0.0429 0.0125 1.0000
17.500 1.4726 0.08371 0.07939 -0.0448 0.0120 1.0000
17.750 1.4620 0.08945 0.08525 -0.0473 0.0115 1.0000
18.000 1.4476 0.09603 0.09197 -0.0502 0.0112 1.0000
18.250 1.4304 0.10335 0.09942 -0.0538 0.0109 1.0000
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