MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 50,000 Max Cl/Cd: 32.35 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh200-il-50000-n5.txt Download as CSV file: xf-mh200-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4167 0.10324 0.09615 -0.0519 1.0000 0.0381
-10.500 -0.4215 0.09861 0.09161 -0.0535 1.0000 0.0375
-10.250 -0.4290 0.09349 0.08658 -0.0554 1.0000 0.0368
-10.000 -0.4395 0.08769 0.08088 -0.0580 1.0000 0.0361
-9.750 -0.4567 0.08165 0.07490 -0.0611 1.0000 0.0354
-9.500 -0.4787 0.07670 0.07002 -0.0628 1.0000 0.0348
-9.250 -0.5048 0.07300 0.06636 -0.0625 1.0000 0.0344
-9.000 -0.5354 0.07051 0.06390 -0.0598 1.0000 0.0339
-8.750 -0.5666 0.06876 0.06217 -0.0555 1.0000 0.0336
-8.500 -0.5936 0.06656 0.05991 -0.0515 1.0000 0.0332
-8.250 -0.6168 0.06410 0.05730 -0.0477 1.0000 0.0329
-8.000 -0.6338 0.06149 0.05449 -0.0443 1.0000 0.0327
-7.750 -0.6463 0.05866 0.05138 -0.0412 1.0000 0.0324
-7.500 -0.6530 0.05575 0.04816 -0.0384 1.0000 0.0323
-7.250 -0.6458 0.05235 0.04435 -0.0379 0.9971 0.0322
-7.000 -0.6286 0.04874 0.04028 -0.0387 0.9921 0.0325
-6.750 -0.6090 0.04559 0.03670 -0.0392 0.9873 0.0328
-6.500 -0.5857 0.04271 0.03339 -0.0399 0.9833 0.0334
-6.250 -0.5635 0.04031 0.03063 -0.0398 0.9789 0.0344
-6.000 -0.5384 0.03829 0.02829 -0.0400 0.9748 0.0365
-5.750 -0.5100 0.03651 0.02605 -0.0404 0.9713 0.0398
-5.500 -0.4842 0.03478 0.02413 -0.0401 0.9678 0.0429
-5.250 -0.4602 0.03339 0.02264 -0.0396 0.9638 0.0462
-5.000 -0.4332 0.03225 0.02123 -0.0394 0.9601 0.0526
-4.750 -0.4062 0.03098 0.01992 -0.0398 0.9567 0.0628
-4.500 -0.3866 0.02973 0.01867 -0.0388 0.9519 0.0799
-4.250 -0.3659 0.02791 0.01730 -0.0387 0.9476 0.1353
-4.000 -0.3487 0.02545 0.01640 -0.0390 0.9438 0.3631
-3.750 -0.3403 0.02503 0.01723 -0.0338 0.9389 0.5730
-3.500 -0.3261 0.02582 0.01813 -0.0289 0.9337 0.6784
-3.250 -0.3032 0.02649 0.01852 -0.0267 0.9293 0.7316
-3.000 -0.2871 0.02692 0.01873 -0.0235 0.9239 0.7645
-2.750 -0.2669 0.02729 0.01882 -0.0211 0.9189 0.7928
-2.500 -0.2408 0.02762 0.01888 -0.0199 0.9149 0.8184
-2.250 -0.2221 0.02780 0.01886 -0.0177 0.9096 0.8402
-2.000 -0.1978 0.02796 0.01880 -0.0166 0.9047 0.8612
-1.750 -0.1634 0.02817 0.01874 -0.0175 0.9011 0.8807
-1.500 -0.1339 0.02829 0.01866 -0.0178 0.8964 0.8994
-1.250 -0.1007 0.02840 0.01857 -0.0191 0.8916 0.9158
-1.000 -0.0556 0.02855 0.01848 -0.0228 0.8880 0.9284
-0.750 -0.0042 0.02870 0.01842 -0.0278 0.8852 0.9380
-0.500 0.0305 0.02880 0.01838 -0.0301 0.8793 0.9485
-0.250 0.0742 0.02892 0.01835 -0.0340 0.8748 0.9576
0.000 0.1276 0.02903 0.01832 -0.0397 0.8715 0.9640
0.250 0.1639 0.02916 0.01837 -0.0425 0.8652 0.9728
0.500 0.2077 0.02926 0.01841 -0.0465 0.8599 0.9803
0.750 0.2574 0.02931 0.01840 -0.0514 0.8561 0.9862
1.000 0.2869 0.02949 0.01857 -0.0530 0.8475 0.9957
1.250 0.3286 0.02954 0.01860 -0.0563 0.8425 1.0000
1.500 0.3323 0.02974 0.01880 -0.0530 0.8316 1.0000
1.750 0.3489 0.02985 0.01892 -0.0516 0.8231 1.0000
2.250 0.3747 0.03010 0.01920 -0.0476 0.8036 1.0000
2.500 0.3958 0.03016 0.01927 -0.0468 0.7951 1.0000
2.750 0.4143 0.03021 0.01935 -0.0455 0.7857 1.0000
3.000 0.4233 0.03039 0.01955 -0.0428 0.7740 1.0000
3.250 0.4429 0.03050 0.01972 -0.0417 0.7637 1.0000
3.500 0.4778 0.03036 0.01965 -0.0428 0.7559 1.0000
4.000 0.5164 0.03062 0.02006 -0.0404 0.7313 1.0000
4.250 0.5419 0.03060 0.02013 -0.0400 0.7193 1.0000
4.500 0.5723 0.03039 0.02003 -0.0400 0.7080 1.0000
4.750 0.6087 0.02994 0.01974 -0.0407 0.6976 1.0000
5.000 0.6335 0.02978 0.01971 -0.0399 0.6834 1.0000
5.250 0.6594 0.02955 0.01961 -0.0392 0.6689 1.0000
5.500 0.6746 0.02969 0.01986 -0.0372 0.6505 1.0000
5.750 0.6972 0.02952 0.01987 -0.0360 0.6330 1.0000
6.000 0.7240 0.02913 0.01964 -0.0351 0.6154 1.0000
6.250 0.7520 0.02865 0.01932 -0.0343 0.5966 1.0000
6.500 0.7752 0.02842 0.01924 -0.0329 0.5734 1.0000
6.750 0.8031 0.02801 0.01899 -0.0320 0.5484 1.0000
7.000 0.8330 0.02757 0.01863 -0.0312 0.5188 1.0000
7.250 0.8627 0.02728 0.01834 -0.0305 0.4847 1.0000
7.500 0.8849 0.02751 0.01850 -0.0291 0.4478 1.0000
7.750 0.9047 0.02797 0.01886 -0.0275 0.4110 1.0000
8.000 0.9186 0.02879 0.01959 -0.0256 0.3759 1.0000
8.250 0.9312 0.02975 0.02045 -0.0237 0.3433 1.0000
8.500 0.9425 0.03085 0.02145 -0.0219 0.3133 1.0000
8.750 0.9528 0.03206 0.02259 -0.0201 0.2852 1.0000
9.000 0.9624 0.03336 0.02384 -0.0183 0.2588 1.0000
9.250 0.9718 0.03475 0.02517 -0.0167 0.2348 1.0000
9.500 0.9803 0.03623 0.02666 -0.0152 0.2120 1.0000
9.750 0.9895 0.03779 0.02823 -0.0138 0.1908 1.0000
10.000 0.9973 0.03946 0.02989 -0.0124 0.1711 1.0000
10.250 1.0056 0.04120 0.03157 -0.0112 0.1542 1.0000
10.500 1.0139 0.04304 0.03350 -0.0100 0.1374 1.0000
10.750 1.0234 0.04494 0.03546 -0.0090 0.1234 1.0000
11.000 1.0321 0.04692 0.03748 -0.0080 0.1113 1.0000
11.250 1.0397 0.04897 0.03956 -0.0071 0.1009 1.0000
11.500 1.0513 0.05113 0.04194 -0.0062 0.0913 1.0000
11.750 1.0598 0.05344 0.04443 -0.0054 0.0835 1.0000
12.000 1.0658 0.05580 0.04688 -0.0047 0.0769 1.0000
12.250 1.0768 0.05850 0.04983 -0.0039 0.0716 1.0000
12.500 1.0808 0.06137 0.05295 -0.0033 0.0668 1.0000
12.750 1.0865 0.06394 0.05545 -0.0029 0.0626 1.0000
13.000 1.0814 0.06792 0.05990 -0.0025 0.0596 1.0000
13.250 1.0771 0.07203 0.06435 -0.0025 0.0573 1.0000
13.500 1.0703 0.07627 0.06884 -0.0028 0.0553 1.0000
13.750 1.0639 0.08041 0.07314 -0.0034 0.0535 1.0000
14.000 1.0630 0.08399 0.07670 -0.0040 0.0512 1.0000
14.250 1.0438 0.09013 0.08317 -0.0061 0.0507 1.0000
14.500 1.0226 0.09704 0.09036 -0.0091 0.0505 1.0000
14.750 1.0006 0.10473 0.09826 -0.0131 0.0506 1.0000
15.000 0.9778 0.11335 0.10706 -0.0180 0.0508 1.0000
15.250 0.9557 0.12274 0.11657 -0.0237 0.0512 1.0000
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Polar data table (+)
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