MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 50,000 Max Cl/Cd: 34.64 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh201-il-50000-n5.txt Download as CSV file: xf-mh201-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4064 0.10466 0.09746 -0.0516 1.0000 0.0398
-10.250 -0.4086 0.10095 0.09383 -0.0520 1.0000 0.0394
-10.000 -0.4139 0.09676 0.08973 -0.0528 1.0000 0.0391
-9.750 -0.4205 0.09253 0.08558 -0.0537 1.0000 0.0386
-9.500 -0.4310 0.08759 0.08074 -0.0552 1.0000 0.0381
-9.250 -0.4455 0.08281 0.07603 -0.0567 1.0000 0.0375
-9.000 -0.4669 0.07845 0.07175 -0.0574 1.0000 0.0371
-8.750 -0.4928 0.07508 0.06844 -0.0566 1.0000 0.0367
-8.500 -0.5217 0.07265 0.06607 -0.0540 1.0000 0.0363
-8.250 -0.5479 0.06973 0.06314 -0.0518 1.0000 0.0360
-8.000 -0.5685 0.06674 0.06007 -0.0495 1.0000 0.0357
-7.750 -0.5852 0.06351 0.05669 -0.0475 1.0000 0.0353
-7.500 -0.5968 0.06011 0.05306 -0.0456 1.0000 0.0352
-7.250 -0.6026 0.05671 0.04938 -0.0440 1.0000 0.0350
-7.000 -0.6030 0.05339 0.04573 -0.0426 1.0000 0.0349
-6.750 -0.5987 0.05013 0.04210 -0.0414 1.0000 0.0350
-6.500 -0.5898 0.04716 0.03871 -0.0404 1.0000 0.0351
-6.250 -0.5690 0.04400 0.03507 -0.0412 0.9973 0.0359
-6.000 -0.5414 0.04126 0.03183 -0.0426 0.9932 0.0375
-5.750 -0.5126 0.03886 0.02881 -0.0436 0.9888 0.0397
-5.500 -0.4839 0.03695 0.02677 -0.0447 0.9849 0.0426
-5.250 -0.4553 0.03529 0.02486 -0.0451 0.9808 0.0450
-5.000 -0.4261 0.03389 0.02309 -0.0452 0.9764 0.0491
-4.750 -0.3966 0.03265 0.02189 -0.0460 0.9724 0.0557
-4.500 -0.3705 0.03150 0.02063 -0.0458 0.9675 0.0628
-4.250 -0.3424 0.03038 0.01947 -0.0464 0.9626 0.0769
-4.000 -0.3122 0.02906 0.01828 -0.0476 0.9584 0.1076
-3.750 -0.2884 0.02714 0.01712 -0.0485 0.9529 0.2053
-3.500 -0.2640 0.02535 0.01677 -0.0494 0.9483 0.4360
-3.250 -0.2518 0.02562 0.01783 -0.0442 0.9421 0.5986
-3.000 -0.2328 0.02632 0.01845 -0.0410 0.9352 0.6809
-2.750 -0.2104 0.02694 0.01884 -0.0387 0.9292 0.7294
-2.500 -0.1925 0.02734 0.01903 -0.0359 0.9218 0.7624
-2.250 -0.1674 0.02772 0.01918 -0.0342 0.9165 0.7913
-2.000 -0.1526 0.02786 0.01914 -0.0313 0.9084 0.8155
-1.750 -0.1277 0.02802 0.01910 -0.0299 0.9026 0.8381
-1.500 -0.1102 0.02806 0.01896 -0.0277 0.8949 0.8598
-1.250 -0.0834 0.02809 0.01882 -0.0269 0.8888 0.8801
-1.000 -0.0567 0.02809 0.01865 -0.0264 0.8823 0.8998
-0.750 -0.0265 0.02808 0.01847 -0.0270 0.8753 0.9171
-0.500 0.0182 0.02810 0.01829 -0.0303 0.8708 0.9305
-0.250 0.0504 0.02814 0.01820 -0.0318 0.8625 0.9429
0.000 0.0988 0.02818 0.01807 -0.0361 0.8572 0.9527
0.250 0.1396 0.02826 0.01803 -0.0393 0.8497 0.9626
0.500 0.1862 0.02830 0.01795 -0.0435 0.8431 0.9711
0.750 0.2343 0.02834 0.01790 -0.0480 0.8366 0.9783
1.000 0.2769 0.02837 0.01789 -0.0515 0.8283 0.9862
1.250 0.3213 0.02835 0.01781 -0.0552 0.8211 0.9939
1.500 0.3512 0.02835 0.01778 -0.0562 0.8116 1.0000
1.750 0.3626 0.02839 0.01781 -0.0540 0.7999 1.0000
2.000 0.3979 0.02816 0.01756 -0.0553 0.7933 1.0000
2.250 0.4057 0.02826 0.01765 -0.0524 0.7803 1.0000
2.500 0.4213 0.02833 0.01772 -0.0508 0.7683 1.0000
2.750 0.4627 0.02800 0.01741 -0.0528 0.7619 1.0000
3.000 0.4793 0.02813 0.01755 -0.0514 0.7487 1.0000
3.250 0.5014 0.02822 0.01767 -0.0507 0.7361 1.0000
3.500 0.5299 0.02817 0.01765 -0.0509 0.7247 1.0000
3.750 0.5703 0.02777 0.01733 -0.0526 0.7159 1.0000
4.000 0.5947 0.02781 0.01742 -0.0521 0.7020 1.0000
4.250 0.6213 0.02778 0.01745 -0.0519 0.6881 1.0000
4.500 0.6493 0.02770 0.01747 -0.0518 0.6740 1.0000
4.750 0.6785 0.02757 0.01741 -0.0518 0.6595 1.0000
5.000 0.7080 0.02740 0.01733 -0.0518 0.6442 1.0000
5.250 0.7382 0.02719 0.01722 -0.0518 0.6280 1.0000
5.500 0.7695 0.02693 0.01705 -0.0519 0.6108 1.0000
5.750 0.8030 0.02661 0.01679 -0.0522 0.5929 1.0000
6.000 0.8267 0.02670 0.01697 -0.0514 0.5710 1.0000
6.250 0.8577 0.02655 0.01686 -0.0513 0.5489 1.0000
6.500 0.8837 0.02665 0.01698 -0.0508 0.5245 1.0000
6.750 0.9121 0.02673 0.01704 -0.0505 0.4992 1.0000
7.000 0.9338 0.02711 0.01742 -0.0494 0.4724 1.0000
7.250 0.9547 0.02759 0.01787 -0.0484 0.4457 1.0000
7.500 0.9750 0.02815 0.01838 -0.0473 0.4195 1.0000
7.750 0.9930 0.02885 0.01904 -0.0459 0.3939 1.0000
8.000 1.0091 0.02968 0.01984 -0.0445 0.3691 1.0000
8.250 1.0255 0.03055 0.02063 -0.0432 0.3460 1.0000
8.500 1.0400 0.03155 0.02167 -0.0417 0.3236 1.0000
8.750 1.0543 0.03260 0.02269 -0.0403 0.3027 1.0000
9.000 1.0687 0.03370 0.02374 -0.0390 0.2836 1.0000
9.250 1.0822 0.03491 0.02500 -0.0377 0.2651 1.0000
9.500 1.0952 0.03616 0.02630 -0.0364 0.2478 1.0000
9.750 1.1087 0.03747 0.02767 -0.0352 0.2320 1.0000
10.000 1.1214 0.03885 0.02909 -0.0341 0.2172 1.0000
10.250 1.1345 0.04028 0.03057 -0.0330 0.2038 1.0000
10.500 1.1475 0.04175 0.03208 -0.0319 0.1915 1.0000
10.750 1.1595 0.04327 0.03364 -0.0308 0.1799 1.0000
11.000 1.1704 0.04500 0.03558 -0.0298 0.1690 1.0000
11.250 1.1811 0.04677 0.03747 -0.0288 0.1592 1.0000
11.500 1.1928 0.04842 0.03908 -0.0279 0.1505 1.0000
11.750 1.1994 0.05060 0.04156 -0.0268 0.1419 1.0000
12.000 1.2089 0.05253 0.04355 -0.0260 0.1345 1.0000
12.250 1.2132 0.05492 0.04619 -0.0250 0.1274 1.0000
12.500 1.2222 0.05703 0.04837 -0.0243 0.1212 1.0000
12.750 1.2211 0.06000 0.05166 -0.0235 0.1153 1.0000
13.000 1.2301 0.06201 0.05365 -0.0229 0.1098 1.0000
13.250 1.2242 0.06573 0.05773 -0.0224 0.1056 1.0000
13.500 1.2190 0.06933 0.06160 -0.0222 0.1014 1.0000
13.750 1.2274 0.07142 0.06364 -0.0219 0.0967 1.0000
14.000 1.2130 0.07637 0.06895 -0.0224 0.0941 1.0000
14.250 1.1947 0.08204 0.07496 -0.0235 0.0920 1.0000
14.500 1.1752 0.08818 0.08139 -0.0254 0.0901 1.0000
14.750 1.1536 0.09505 0.08849 -0.0281 0.0886 1.0000
15.000 1.1212 0.10447 0.09814 -0.0328 0.0883 1.0000
15.250 1.0417 0.12585 0.11971 -0.0459 0.0914 1.0000
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Polar data table (+)
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