MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 500,000 Max Cl/Cd: 98.55 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh200-il-500000.txt Download as CSV file: xf-mh200-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3088 0.11105 0.10888 -0.0491 1.0000 0.0164
-12.000 -0.3120 0.10664 0.10450 -0.0503 1.0000 0.0164
-7.250 -0.3982 0.02268 0.01730 -0.0870 0.8933 0.0153
-7.000 -0.3774 0.01897 0.01301 -0.0852 0.8869 0.0123
-6.750 -0.3527 0.01842 0.01229 -0.0845 0.8807 0.0119
-6.500 -0.3288 0.01718 0.01095 -0.0839 0.8749 0.0115
-6.250 -0.3057 0.01579 0.00943 -0.0832 0.8703 0.0114
-6.000 -0.2840 0.01478 0.00836 -0.0823 0.8649 0.0113
-5.750 -0.2617 0.01396 0.00746 -0.0814 0.8600 0.0114
-5.500 -0.2383 0.01331 0.00670 -0.0808 0.8558 0.0116
-5.250 -0.2173 0.01248 0.00579 -0.0798 0.8509 0.0121
-5.000 -0.1941 0.01182 0.00506 -0.0792 0.8466 0.0134
-4.750 -0.1686 0.01143 0.00459 -0.0789 0.8430 0.0160
-4.500 -0.1476 0.01038 0.00383 -0.0780 0.8391 0.0813
-4.250 -0.1262 0.00950 0.00349 -0.0776 0.8349 0.2028
-4.000 -0.1034 0.00873 0.00320 -0.0774 0.8312 0.3276
-3.750 -0.0799 0.00803 0.00297 -0.0772 0.8279 0.4588
-3.500 -0.0560 0.00751 0.00289 -0.0768 0.8244 0.5752
-3.250 -0.0298 0.00736 0.00292 -0.0765 0.8206 0.6398
-3.000 -0.0022 0.00737 0.00296 -0.0764 0.8173 0.6742
-2.750 0.0262 0.00743 0.00297 -0.0764 0.8143 0.6946
-2.500 0.0544 0.00751 0.00301 -0.0765 0.8111 0.7099
-2.250 0.0822 0.00757 0.00305 -0.0764 0.8075 0.7222
-2.000 0.1104 0.00763 0.00308 -0.0764 0.8040 0.7328
-1.750 0.1391 0.00771 0.00308 -0.0766 0.8009 0.7429
-1.500 0.1673 0.00780 0.00314 -0.0766 0.7979 0.7501
-1.250 0.1951 0.00784 0.00317 -0.0766 0.7939 0.7582
-1.000 0.2227 0.00789 0.00321 -0.0764 0.7898 0.7644
-0.750 0.2515 0.00794 0.00320 -0.0766 0.7859 0.7716
-0.500 0.2790 0.00799 0.00325 -0.0765 0.7819 0.7768
-0.250 0.3065 0.00803 0.00329 -0.0764 0.7771 0.7834
0.000 0.3343 0.00805 0.00330 -0.0763 0.7727 0.7895
0.250 0.3623 0.00812 0.00335 -0.0762 0.7686 0.7950
0.500 0.3899 0.00813 0.00336 -0.0763 0.7633 0.8006
0.750 0.4175 0.00812 0.00335 -0.0761 0.7580 0.8043
1.000 0.4451 0.00814 0.00337 -0.0760 0.7527 0.8083
1.250 0.4726 0.00813 0.00336 -0.0760 0.7462 0.8127
1.500 0.5011 0.00814 0.00333 -0.0761 0.7408 0.8166
1.750 0.5274 0.00812 0.00337 -0.0758 0.7341 0.8201
2.000 0.5550 0.00812 0.00337 -0.0757 0.7279 0.8242
2.250 0.5826 0.00813 0.00340 -0.0757 0.7211 0.8287
2.500 0.6096 0.00811 0.00339 -0.0755 0.7139 0.8322
2.750 0.6361 0.00810 0.00344 -0.0752 0.7060 0.8355
3.000 0.6633 0.00810 0.00343 -0.0751 0.6976 0.8391
3.250 0.6902 0.00809 0.00346 -0.0750 0.6873 0.8428
3.500 0.7167 0.00808 0.00348 -0.0747 0.6761 0.8459
3.750 0.7424 0.00808 0.00351 -0.0743 0.6627 0.8488
4.000 0.7680 0.00810 0.00355 -0.0738 0.6463 0.8522
4.250 0.7931 0.00816 0.00358 -0.0733 0.6250 0.8558
4.500 0.8170 0.00829 0.00364 -0.0726 0.5944 0.8592
4.750 0.8376 0.00852 0.00375 -0.0712 0.5571 0.8625
5.000 0.8574 0.00887 0.00395 -0.0697 0.5164 0.8662
5.250 0.8759 0.00932 0.00420 -0.0681 0.4705 0.8703
5.500 0.8941 0.00979 0.00450 -0.0665 0.4260 0.8743
5.750 0.9113 0.01025 0.00481 -0.0647 0.3843 0.8782
6.000 0.9289 0.01074 0.00515 -0.0631 0.3439 0.8827
6.250 0.9468 0.01125 0.00550 -0.0616 0.3060 0.8876
6.500 0.9636 0.01170 0.00584 -0.0597 0.2743 0.8921
6.750 0.9810 0.01216 0.00621 -0.0581 0.2453 0.8974
7.000 0.9978 0.01264 0.00659 -0.0564 0.2174 0.9031
7.250 1.0132 0.01308 0.00696 -0.0544 0.1948 0.9096
7.500 1.0288 0.01348 0.00732 -0.0524 0.1742 0.9169
7.750 1.0412 0.01387 0.00768 -0.0497 0.1567 0.9260
8.000 1.0525 0.01428 0.00806 -0.0469 0.1397 0.9385
8.250 1.0651 0.01469 0.00848 -0.0444 0.1222 0.9599
8.500 1.0871 0.01532 0.00904 -0.0442 0.1024 1.0000
8.750 1.1055 0.01601 0.00965 -0.0434 0.0855 1.0000
9.000 1.1224 0.01674 0.01031 -0.0423 0.0703 1.0000
9.250 1.1377 0.01753 0.01104 -0.0409 0.0579 1.0000
9.500 1.1521 0.01835 0.01184 -0.0394 0.0485 1.0000
9.750 1.1633 0.01937 0.01281 -0.0375 0.0407 1.0000
10.000 1.1799 0.02003 0.01356 -0.0364 0.0369 1.0000
10.250 1.1911 0.02106 0.01457 -0.0346 0.0325 1.0000
10.500 1.2043 0.02195 0.01553 -0.0332 0.0293 1.0000
10.750 1.2192 0.02274 0.01635 -0.0320 0.0262 1.0000
11.000 1.2247 0.02421 0.01784 -0.0298 0.0228 1.0000
11.250 1.2427 0.02479 0.01849 -0.0291 0.0210 1.0000
11.500 1.2574 0.02562 0.01932 -0.0282 0.0183 1.0000
11.750 1.2619 0.02724 0.02101 -0.0262 0.0163 1.0000
12.000 1.2787 0.02794 0.02177 -0.0256 0.0145 1.0000
12.250 1.2901 0.02908 0.02294 -0.0245 0.0127 1.0000
12.500 1.2936 0.03089 0.02484 -0.0228 0.0112 1.0000
12.750 1.3052 0.03205 0.02609 -0.0219 0.0098 1.0000
13.000 1.3111 0.03373 0.02782 -0.0206 0.0085 1.0000
13.250 1.3141 0.03574 0.02992 -0.0193 0.0073 1.0000
13.500 1.3207 0.03746 0.03173 -0.0184 0.0062 1.0000
13.750 1.3207 0.03983 0.03419 -0.0173 0.0056 1.0000
14.000 1.3157 0.04281 0.03731 -0.0161 0.0051 1.0000
14.250 1.3174 0.04522 0.03985 -0.0155 0.0047 1.0000
14.500 1.3203 0.04759 0.04231 -0.0151 0.0040 1.0000
14.750 1.3163 0.05082 0.04569 -0.0148 0.0042 1.0000
15.000 1.3127 0.05417 0.04915 -0.0148 0.0038 1.0000
15.250 1.3075 0.05790 0.05300 -0.0152 0.0037 1.0000
15.500 1.2959 0.06267 0.05795 -0.0160 0.0036 1.0000
15.750 1.2751 0.06912 0.06458 -0.0176 0.0034 1.0000
16.000 1.2672 0.07399 0.06960 -0.0192 0.0034 1.0000
16.250 1.2610 0.07890 0.07467 -0.0211 0.0032 1.0000
16.500 1.2514 0.08454 0.08047 -0.0236 0.0032 1.0000
16.750 1.2389 0.09086 0.08694 -0.0264 0.0033 1.0000
17.000 1.2283 0.09717 0.09342 -0.0296 0.0031 1.0000
17.250 1.2149 0.10412 0.10051 -0.0331 0.0032 1.0000
17.500 1.2013 0.11132 0.10786 -0.0370 0.0031 1.0000
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Polar data table (+)
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