MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 500,000 Max Cl/Cd: 85.66 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh200-il-500000-n5.txt Download as CSV file: xf-mh200-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4666 0.08743 0.08518 -0.0529 1.0000 0.0045
-11.000 -0.5452 0.06063 0.05826 -0.0684 1.0000 0.0041
-10.750 -0.5752 0.05263 0.05008 -0.0737 0.9991 0.0041
-10.250 -0.6152 0.03758 0.03425 -0.0841 0.9642 0.0040
-10.000 -0.6094 0.03277 0.02898 -0.0874 0.9448 0.0040
-9.750 -0.5945 0.02932 0.02510 -0.0893 0.9278 0.0041
-9.500 -0.5791 0.02723 0.02270 -0.0894 0.9107 0.0042
-9.250 -0.5678 0.02508 0.02018 -0.0881 0.8954 0.0042
-9.000 -0.5506 0.02416 0.01909 -0.0872 0.8839 0.0044
-8.750 -0.5346 0.02290 0.01758 -0.0860 0.8735 0.0047
-8.500 -0.5177 0.02153 0.01596 -0.0848 0.8649 0.0048
-8.250 -0.4985 0.02049 0.01469 -0.0838 0.8571 0.0050
-8.000 -0.4790 0.01935 0.01335 -0.0828 0.8500 0.0051
-7.750 -0.4585 0.01835 0.01217 -0.0819 0.8434 0.0052
-7.500 -0.4378 0.01735 0.01102 -0.0810 0.8377 0.0052
-7.250 -0.4166 0.01649 0.01004 -0.0802 0.8322 0.0052
-7.000 -0.3951 0.01570 0.00911 -0.0794 0.8275 0.0053
-6.750 -0.3731 0.01500 0.00832 -0.0787 0.8227 0.0053
-6.500 -0.3508 0.01436 0.00758 -0.0780 0.8180 0.0054
-6.250 -0.3278 0.01379 0.00692 -0.0774 0.8137 0.0055
-6.000 -0.3049 0.01316 0.00621 -0.0768 0.8096 0.0057
-5.750 -0.2814 0.01260 0.00558 -0.0763 0.8057 0.0060
-5.500 -0.2566 0.01219 0.00511 -0.0760 0.8022 0.0065
-5.250 -0.2311 0.01185 0.00469 -0.0757 0.7990 0.0071
-5.000 -0.2052 0.01154 0.00431 -0.0755 0.7956 0.0080
-4.750 -0.1795 0.01119 0.00393 -0.0753 0.7920 0.0104
-4.500 -0.1536 0.01086 0.00361 -0.0752 0.7888 0.0179
-4.250 -0.1285 0.01042 0.00329 -0.0750 0.7858 0.0484
-4.000 -0.1045 0.00979 0.00298 -0.0748 0.7829 0.1227
-3.750 -0.0803 0.00918 0.00273 -0.0748 0.7796 0.2119
-3.500 -0.0557 0.00859 0.00251 -0.0747 0.7763 0.3089
-3.250 -0.0303 0.00810 0.00232 -0.0747 0.7730 0.3970
-3.000 -0.0041 0.00771 0.00215 -0.0748 0.7701 0.4736
-2.750 0.0227 0.00744 0.00205 -0.0748 0.7671 0.5320
-2.500 0.0498 0.00724 0.00200 -0.0749 0.7637 0.5833
-2.250 0.0774 0.00713 0.00199 -0.0749 0.7603 0.6230
-2.000 0.1053 0.00710 0.00199 -0.0749 0.7573 0.6517
-1.750 0.1337 0.00711 0.00198 -0.0750 0.7544 0.6714
-1.500 0.1620 0.00711 0.00199 -0.0751 0.7509 0.6860
-1.250 0.1904 0.00712 0.00199 -0.0753 0.7472 0.6984
-1.000 0.2187 0.00715 0.00200 -0.0754 0.7434 0.7082
-0.750 0.2471 0.00718 0.00200 -0.0755 0.7395 0.7167
-0.500 0.2753 0.00720 0.00201 -0.0756 0.7345 0.7248
-0.250 0.3035 0.00722 0.00203 -0.0757 0.7297 0.7323
0.000 0.3318 0.00727 0.00204 -0.0758 0.7252 0.7407
0.250 0.3597 0.00729 0.00208 -0.0758 0.7198 0.7466
0.500 0.3878 0.00732 0.00209 -0.0759 0.7143 0.7519
0.750 0.4161 0.00735 0.00210 -0.0761 0.7084 0.7569
1.000 0.4437 0.00736 0.00213 -0.0760 0.7010 0.7605
1.250 0.4714 0.00739 0.00216 -0.0760 0.6935 0.7644
1.500 0.4991 0.00742 0.00218 -0.0761 0.6852 0.7686
1.750 0.5269 0.00745 0.00221 -0.0761 0.6764 0.7728
2.000 0.5539 0.00749 0.00226 -0.0760 0.6670 0.7765
2.250 0.5811 0.00754 0.00231 -0.0759 0.6555 0.7807
2.500 0.6082 0.00760 0.00235 -0.0758 0.6415 0.7846
2.750 0.6346 0.00767 0.00240 -0.0755 0.6238 0.7877
3.000 0.6596 0.00779 0.00246 -0.0750 0.5990 0.7905
3.250 0.6835 0.00798 0.00255 -0.0743 0.5692 0.7935
3.500 0.7067 0.00825 0.00269 -0.0735 0.5358 0.7967
3.750 0.7289 0.00859 0.00288 -0.0726 0.4987 0.8000
4.000 0.7508 0.00893 0.00309 -0.0716 0.4625 0.8027
4.250 0.7719 0.00931 0.00334 -0.0705 0.4253 0.8055
4.500 0.7933 0.00970 0.00359 -0.0695 0.3895 0.8086
4.750 0.8144 0.01011 0.00387 -0.0685 0.3546 0.8119
5.000 0.8361 0.01051 0.00415 -0.0676 0.3237 0.8153
5.250 0.8568 0.01090 0.00444 -0.0665 0.2928 0.8180
5.500 0.8773 0.01131 0.00475 -0.0654 0.2630 0.8211
5.750 0.8980 0.01172 0.00507 -0.0643 0.2374 0.8246
6.000 0.9189 0.01212 0.00539 -0.0633 0.2136 0.8283
6.250 0.9390 0.01254 0.00573 -0.0622 0.1908 0.8315
6.500 0.9590 0.01293 0.00607 -0.0610 0.1716 0.8349
6.750 0.9786 0.01334 0.00645 -0.0598 0.1539 0.8390
7.000 0.9977 0.01379 0.00683 -0.0585 0.1341 0.8433
7.250 1.0155 0.01422 0.00721 -0.0570 0.1177 0.8471
7.500 1.0320 0.01463 0.00761 -0.0552 0.1037 0.8518
7.750 1.0487 0.01507 0.00803 -0.0534 0.0916 0.8572
8.000 1.0645 0.01554 0.00849 -0.0516 0.0796 0.8625
8.250 1.0798 0.01605 0.00900 -0.0497 0.0680 0.8685
8.500 1.0952 0.01656 0.00952 -0.0479 0.0588 0.8750
8.750 1.1095 0.01710 0.01008 -0.0459 0.0508 0.8829
9.000 1.1240 0.01762 0.01064 -0.0439 0.0441 0.8922
9.250 1.1373 0.01818 0.01124 -0.0419 0.0383 0.9041
9.500 1.1488 0.01874 0.01185 -0.0395 0.0333 0.9213
10.000 1.1804 0.01997 0.01322 -0.0368 0.0260 1.0000
10.250 1.1945 0.02080 0.01406 -0.0354 0.0228 1.0000
10.500 1.2103 0.02150 0.01482 -0.0343 0.0205 1.0000
10.750 1.2238 0.02237 0.01570 -0.0330 0.0177 1.0000
11.000 1.2375 0.02324 0.01661 -0.0317 0.0156 1.0000
11.250 1.2511 0.02413 0.01753 -0.0305 0.0135 1.0000
11.500 1.2629 0.02516 0.01858 -0.0292 0.0112 1.0000
11.750 1.2758 0.02612 0.01961 -0.0280 0.0101 1.0000
12.000 1.2867 0.02725 0.02076 -0.0268 0.0083 1.0000
12.250 1.2978 0.02839 0.02198 -0.0256 0.0070 1.0000
12.500 1.3083 0.02960 0.02326 -0.0244 0.0063 1.0000
12.750 1.3173 0.03095 0.02466 -0.0232 0.0054 1.0000
13.000 1.3263 0.03233 0.02613 -0.0221 0.0048 1.0000
13.250 1.3342 0.03383 0.02772 -0.0210 0.0041 1.0000
13.500 1.3400 0.03556 0.02952 -0.0199 0.0035 1.0000
13.750 1.3461 0.03731 0.03136 -0.0189 0.0032 1.0000
14.000 1.3512 0.03917 0.03334 -0.0180 0.0029 1.0000
14.250 1.3551 0.04121 0.03548 -0.0172 0.0025 1.0000
14.500 1.3567 0.04356 0.03792 -0.0165 0.0021 1.0000
14.750 1.3602 0.04577 0.04027 -0.0159 0.0022 1.0000
15.000 1.3584 0.04865 0.04327 -0.0155 0.0019 1.0000
15.250 1.3590 0.05139 0.04614 -0.0153 0.0019 1.0000
15.500 1.3582 0.05440 0.04929 -0.0153 0.0018 1.0000
15.750 1.3549 0.05785 0.05289 -0.0156 0.0016 1.0000
16.000 1.3521 0.06141 0.05658 -0.0162 0.0016 1.0000
16.250 1.3470 0.06546 0.06077 -0.0171 0.0015 1.0000
16.500 1.3411 0.06981 0.06526 -0.0184 0.0014 1.0000
16.750 1.3335 0.07464 0.07025 -0.0201 0.0014 1.0000
17.000 1.3232 0.08012 0.07587 -0.0222 0.0013 1.0000
17.250 1.3131 0.08583 0.08175 -0.0247 0.0013 1.0000
17.500 1.2992 0.09242 0.08850 -0.0279 0.0013 1.0000
17.750 1.2843 0.09950 0.09574 -0.0315 0.0013 1.0000
18.000 1.2687 0.10695 0.10335 -0.0354 0.0013 1.0000
18.250 1.2509 0.11503 0.11160 -0.0399 0.0013 1.0000
18.500 1.2324 0.12351 0.12024 -0.0447 0.0013 1.0000
18.750 1.2135 0.13229 0.12917 -0.0497 0.0013 1.0000
19.000 1.1924 0.14172 0.13875 -0.0553 0.0013 1.0000
19.250 1.1750 0.15052 0.14769 -0.0606 0.0014 1.0000
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Polar data table (+)
Polar graphs
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