MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 200,000 Max Cl/Cd: 73.46 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh201-il-200000.txt Download as CSV file: xf-mh201-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4161 0.09149 0.08823 -0.0447 1.0000 0.0543
-9.000 -0.4314 0.08844 0.08526 -0.0439 1.0000 0.0554
-8.750 -0.4521 0.08538 0.08229 -0.0430 1.0000 0.0560
-8.500 -0.4769 0.08231 0.07930 -0.0421 1.0000 0.0561
-8.250 -0.4024 0.06079 0.05790 -0.0607 0.9860 0.0628
-8.000 -0.4236 0.05499 0.05200 -0.0652 0.9782 0.0631
-7.750 -0.4236 0.04971 0.04659 -0.0697 0.9723 0.0647
-7.500 -0.4289 0.04519 0.04188 -0.0718 0.9633 0.0673
-7.250 -0.4862 0.05397 0.05024 -0.0700 0.9667 0.0656
-7.000 -0.4741 0.04892 0.04460 -0.0741 0.9603 0.0734
-6.750 -0.4541 0.04618 0.04191 -0.0746 0.9554 0.0759
-6.500 -0.4371 0.03123 0.02450 -0.0725 0.9493 0.0266
-6.250 -0.4045 0.02835 0.02141 -0.0740 0.9472 0.0257
-6.000 -0.3692 0.02600 0.01878 -0.0757 0.9456 0.0249
-5.750 -0.3501 0.02457 0.01716 -0.0742 0.9386 0.0248
-5.500 -0.3174 0.02305 0.01545 -0.0750 0.9355 0.0253
-5.250 -0.2819 0.02178 0.01406 -0.0765 0.9333 0.0259
-5.000 -0.2461 0.02028 0.01258 -0.0783 0.9315 0.0279
-4.750 -0.2273 0.01980 0.01209 -0.0770 0.9240 0.0319
-4.500 -0.1938 0.01872 0.01105 -0.0786 0.9208 0.0380
-4.250 -0.1566 0.01735 0.00976 -0.0809 0.9185 0.0613
-4.000 -0.1194 0.01494 0.00873 -0.0848 0.9170 0.3165
-3.750 -0.0992 0.01411 0.00865 -0.0842 0.9102 0.4851
-3.500 -0.0688 0.01382 0.00887 -0.0843 0.9064 0.6143
-3.250 -0.0335 0.01400 0.00911 -0.0849 0.9039 0.6784
-3.000 0.0052 0.01421 0.00924 -0.0861 0.9021 0.7109
-2.750 0.0228 0.01457 0.00955 -0.0836 0.8942 0.7289
-2.500 0.0560 0.01473 0.00963 -0.0839 0.8908 0.7456
-2.250 0.0922 0.01482 0.00965 -0.0848 0.8883 0.7597
-2.000 0.1294 0.01483 0.00958 -0.0858 0.8864 0.7724
-1.750 0.1462 0.01505 0.00975 -0.0834 0.8775 0.7843
-1.500 0.1783 0.01504 0.00970 -0.0834 0.8740 0.7937
-1.250 0.2148 0.01492 0.00951 -0.0844 0.8714 0.8030
-1.000 0.2343 0.01505 0.00959 -0.0826 0.8629 0.8136
-0.750 0.2634 0.01495 0.00947 -0.0819 0.8585 0.8210
-0.500 0.3006 0.01478 0.00923 -0.0832 0.8554 0.8308
-0.250 0.3142 0.01487 0.00933 -0.0799 0.8458 0.8389
0.000 0.3499 0.01465 0.00905 -0.0811 0.8415 0.8465
0.250 0.3703 0.01461 0.00901 -0.0792 0.8334 0.8529
0.500 0.4045 0.01443 0.00877 -0.0803 0.8273 0.8599
0.750 0.4287 0.01429 0.00862 -0.0791 0.8201 0.8649
1.000 0.4565 0.01413 0.00844 -0.0788 0.8123 0.8710
1.250 0.4851 0.01399 0.00827 -0.0788 0.8047 0.8767
1.500 0.5104 0.01381 0.00808 -0.0778 0.7961 0.8820
1.750 0.5371 0.01371 0.00797 -0.0775 0.7870 0.8881
2.000 0.5662 0.01349 0.00772 -0.0774 0.7788 0.8928
2.250 0.5876 0.01338 0.00763 -0.0759 0.7680 0.8984
2.500 0.6175 0.01324 0.00746 -0.0762 0.7586 0.9035
2.750 0.6429 0.01305 0.00727 -0.0754 0.7480 0.9078
3.000 0.6653 0.01292 0.00715 -0.0742 0.7357 0.9130
3.250 0.6915 0.01281 0.00704 -0.0738 0.7233 0.9179
3.500 0.7156 0.01265 0.00687 -0.0729 0.7107 0.9223
3.750 0.7397 0.01250 0.00674 -0.0720 0.6967 0.9273
4.000 0.7642 0.01241 0.00665 -0.0713 0.6809 0.9324
4.250 0.7854 0.01228 0.00652 -0.0698 0.6637 0.9375
4.500 0.8078 0.01219 0.00645 -0.0686 0.6446 0.9432
4.750 0.8313 0.01214 0.00634 -0.0677 0.6239 0.9485
5.000 0.8526 0.01213 0.00631 -0.0664 0.6003 0.9551
5.250 0.8757 0.01221 0.00632 -0.0655 0.5748 0.9614
5.500 0.8998 0.01237 0.00638 -0.0649 0.5469 0.9684
5.750 0.9259 0.01263 0.00655 -0.0649 0.5163 0.9760
6.000 0.9535 0.01298 0.00680 -0.0654 0.4836 0.9850
6.250 0.9776 0.01336 0.00708 -0.0652 0.4514 1.0000
6.500 0.9969 0.01384 0.00743 -0.0643 0.4213 1.0000
6.750 1.0171 0.01438 0.00784 -0.0636 0.3912 1.0000
7.000 1.0375 0.01495 0.00832 -0.0629 0.3620 1.0000
7.250 1.0573 0.01555 0.00882 -0.0622 0.3341 1.0000
7.500 1.0768 0.01619 0.00937 -0.0615 0.3080 1.0000
7.750 1.0950 0.01692 0.00997 -0.0605 0.2841 1.0000
8.000 1.1144 0.01761 0.01063 -0.0598 0.2608 1.0000
8.250 1.1318 0.01840 0.01132 -0.0588 0.2402 1.0000
8.500 1.1494 0.01919 0.01205 -0.0578 0.2209 1.0000
8.750 1.1664 0.01999 0.01281 -0.0568 0.2030 1.0000
9.000 1.1824 0.02085 0.01364 -0.0556 0.1871 1.0000
9.250 1.1977 0.02175 0.01451 -0.0543 0.1728 1.0000
9.500 1.2121 0.02271 0.01543 -0.0530 0.1601 1.0000
9.750 1.2254 0.02374 0.01641 -0.0515 0.1488 1.0000
10.000 1.2390 0.02474 0.01742 -0.0501 0.1383 1.0000
10.250 1.2532 0.02572 0.01847 -0.0488 0.1286 1.0000
10.500 1.2650 0.02693 0.01964 -0.0473 0.1203 1.0000
10.750 1.2773 0.02801 0.02077 -0.0460 0.1124 1.0000
11.000 1.2892 0.02927 0.02207 -0.0446 0.1052 1.0000
11.250 1.2999 0.03052 0.02334 -0.0432 0.0987 1.0000
11.500 1.3109 0.03190 0.02481 -0.0419 0.0925 1.0000
11.750 1.3206 0.03323 0.02620 -0.0406 0.0868 1.0000
12.000 1.3301 0.03485 0.02785 -0.0393 0.0815 1.0000
12.250 1.3389 0.03628 0.02940 -0.0381 0.0764 1.0000
12.500 1.3469 0.03817 0.03122 -0.0369 0.0716 1.0000
12.750 1.3543 0.03976 0.03304 -0.0357 0.0676 1.0000
13.000 1.3604 0.04152 0.03486 -0.0347 0.0637 1.0000
13.250 1.3672 0.04367 0.03703 -0.0337 0.0599 1.0000
13.500 1.3719 0.04566 0.03924 -0.0327 0.0567 1.0000
13.750 1.3757 0.04775 0.04141 -0.0320 0.0536 1.0000
14.000 1.3819 0.05020 0.04382 -0.0312 0.0504 1.0000
14.250 1.3826 0.05272 0.04661 -0.0305 0.0482 1.0000
14.500 1.3839 0.05529 0.04933 -0.0301 0.0458 1.0000
14.750 1.3853 0.05792 0.05199 -0.0299 0.0436 1.0000
15.000 1.3874 0.06098 0.05512 -0.0295 0.0413 1.0000
15.250 1.3839 0.06438 0.05878 -0.0296 0.0397 1.0000
15.500 1.3808 0.06786 0.06246 -0.0300 0.0380 1.0000
15.750 1.3791 0.07122 0.06591 -0.0306 0.0364 1.0000
16.000 1.3792 0.07455 0.06923 -0.0310 0.0346 1.0000
16.250 1.3715 0.07916 0.07407 -0.0320 0.0335 1.0000
16.500 1.3623 0.08408 0.07924 -0.0337 0.0324 1.0000
16.750 1.3530 0.08918 0.08456 -0.0356 0.0314 1.0000
17.000 1.3454 0.09415 0.08969 -0.0378 0.0303 1.0000
17.250 1.3412 0.09861 0.09421 -0.0399 0.0291 1.0000
17.500 1.3393 0.10265 0.09823 -0.0413 0.0278 1.0000
17.750 1.3240 0.10946 0.10528 -0.0449 0.0273 1.0000
18.000 1.3077 0.11674 0.11282 -0.0491 0.0269 1.0000
18.250 1.2906 0.12446 0.12078 -0.0538 0.0265 1.0000
18.500 1.2723 0.13274 0.12929 -0.0590 0.0263 1.0000
18.750 1.2514 0.14195 0.13872 -0.0651 0.0262 1.0000
19.000 1.2266 0.15246 0.14945 -0.0723 0.0264 1.0000
19.250 1.1971 0.16469 0.16187 -0.0807 0.0270 1.0000
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