MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 100,000 Max Cl/Cd: 50.96 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh200-il-100000-n5.txt Download as CSV file: xf-mh200-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4242 0.09524 0.09023 -0.0529 1.0000 0.0188
-10.500 -0.4355 0.08860 0.08367 -0.0557 1.0000 0.0182
-10.000 -0.5025 0.06764 0.06256 -0.0684 1.0000 0.0164
-9.750 -0.5246 0.06437 0.05926 -0.0678 1.0000 0.0163
-9.500 -0.5480 0.06229 0.05721 -0.0651 1.0000 0.0163
-9.250 -0.5780 0.06136 0.05631 -0.0600 1.0000 0.0163
-9.000 -0.5821 0.05709 0.05180 -0.0628 0.9893 0.0161
-8.750 -0.5795 0.05250 0.04687 -0.0652 0.9788 0.0160
-8.500 -0.5714 0.04839 0.04234 -0.0671 0.9705 0.0160
-8.250 -0.5632 0.04483 0.03838 -0.0674 0.9612 0.0159
-8.000 -0.5474 0.04121 0.03428 -0.0684 0.9553 0.0159
-7.750 -0.5326 0.03834 0.03099 -0.0681 0.9479 0.0159
-7.500 -0.5093 0.03541 0.02758 -0.0689 0.9439 0.0160
-7.250 -0.4883 0.03315 0.02493 -0.0686 0.9381 0.0162
-7.000 -0.4633 0.03095 0.02241 -0.0688 0.9335 0.0165
-6.750 -0.4352 0.02890 0.02020 -0.0698 0.9303 0.0173
-6.500 -0.4094 0.02763 0.01878 -0.0702 0.9261 0.0190
-6.250 -0.3863 0.02652 0.01750 -0.0697 0.9208 0.0210
-6.000 -0.3582 0.02529 0.01609 -0.0700 0.9173 0.0225
-5.750 -0.3310 0.02376 0.01451 -0.0705 0.9144 0.0243
-5.500 -0.3131 0.02290 0.01357 -0.0692 0.9078 0.0266
-5.250 -0.2879 0.02204 0.01257 -0.0691 0.9036 0.0319
-5.000 -0.2606 0.02100 0.01144 -0.0695 0.9006 0.0419
-4.750 -0.2427 0.01993 0.01060 -0.0683 0.8950 0.0745
-4.500 -0.2251 0.01848 0.00998 -0.0676 0.8901 0.2155
-4.250 -0.2045 0.01716 0.00959 -0.0673 0.8867 0.3955
-4.000 -0.1878 0.01663 0.00974 -0.0650 0.8821 0.5402
-3.750 -0.1686 0.01679 0.01010 -0.0625 0.8771 0.6184
-3.500 -0.1419 0.01700 0.01024 -0.0616 0.8737 0.6635
-3.250 -0.1123 0.01717 0.01025 -0.0615 0.8711 0.6955
-3.000 -0.0936 0.01745 0.01041 -0.0595 0.8654 0.7173
-2.750 -0.0691 0.01766 0.01047 -0.0585 0.8611 0.7361
-2.500 -0.0408 0.01780 0.01047 -0.0582 0.8581 0.7527
-2.250 -0.0144 0.01795 0.01050 -0.0575 0.8547 0.7667
-2.000 0.0032 0.01817 0.01065 -0.0554 0.8487 0.7791
-1.750 0.0295 0.01827 0.01063 -0.0548 0.8451 0.7912
-1.500 0.0587 0.01832 0.01057 -0.0547 0.8423 0.8032
-1.250 0.0752 0.01852 0.01071 -0.0526 0.8361 0.8151
-1.000 0.0989 0.01861 0.01075 -0.0514 0.8317 0.8241
-0.750 0.1281 0.01859 0.01064 -0.0515 0.8286 0.8330
-0.500 0.1484 0.01870 0.01070 -0.0501 0.8231 0.8416
-0.250 0.1711 0.01875 0.01072 -0.0491 0.8179 0.8489
0.000 0.2009 0.01869 0.01059 -0.0494 0.8145 0.8562
0.250 0.2228 0.01876 0.01063 -0.0483 0.8089 0.8631
0.500 0.2457 0.01879 0.01064 -0.0474 0.8031 0.8707
0.750 0.2771 0.01868 0.01050 -0.0479 0.7996 0.8765
1.000 0.2961 0.01877 0.01059 -0.0464 0.7923 0.8840
1.250 0.3244 0.01868 0.01050 -0.0464 0.7871 0.8900
1.500 0.3595 0.01850 0.01030 -0.0476 0.7837 0.8948
1.750 0.3749 0.01862 0.01046 -0.0455 0.7744 0.9025
2.000 0.4098 0.01840 0.01025 -0.0466 0.7701 0.9067
2.250 0.4286 0.01847 0.01036 -0.0451 0.7611 0.9139
2.500 0.4632 0.01823 0.01014 -0.0461 0.7560 0.9182
2.750 0.4850 0.01824 0.01022 -0.0451 0.7464 0.9247
3.000 0.5205 0.01793 0.00993 -0.0462 0.7406 0.9295
3.250 0.5445 0.01789 0.00997 -0.0456 0.7296 0.9354
3.500 0.5711 0.01776 0.00993 -0.0454 0.7194 0.9419
3.750 0.6060 0.01748 0.00971 -0.0464 0.7105 0.9464
4.000 0.6352 0.01735 0.00966 -0.0467 0.6987 0.9525
4.250 0.6636 0.01725 0.00968 -0.0469 0.6854 0.9592
4.500 0.6947 0.01714 0.00967 -0.0476 0.6711 0.9657
4.750 0.7265 0.01700 0.00964 -0.0484 0.6550 0.9725
5.000 0.7563 0.01698 0.00976 -0.0491 0.6343 0.9813
5.250 0.7892 0.01681 0.00967 -0.0501 0.6114 0.9911
5.500 0.8117 0.01674 0.00960 -0.0492 0.5850 1.0000
5.750 0.8321 0.01670 0.00951 -0.0477 0.5552 1.0000
6.000 0.8526 0.01683 0.00956 -0.0464 0.5195 1.0000
6.250 0.8725 0.01712 0.00970 -0.0451 0.4807 1.0000
6.500 0.8903 0.01759 0.00999 -0.0436 0.4403 1.0000
6.750 0.9067 0.01818 0.01042 -0.0420 0.4010 1.0000
7.000 0.9220 0.01885 0.01094 -0.0403 0.3641 1.0000
7.250 0.9364 0.01957 0.01154 -0.0386 0.3297 1.0000
7.500 0.9494 0.02033 0.01217 -0.0366 0.2982 1.0000
7.750 0.9624 0.02114 0.01287 -0.0348 0.2690 1.0000
8.000 0.9758 0.02197 0.01362 -0.0331 0.2425 1.0000
8.250 0.9891 0.02285 0.01443 -0.0315 0.2180 1.0000
8.500 1.0016 0.02380 0.01531 -0.0298 0.1953 1.0000
8.750 1.0149 0.02475 0.01623 -0.0283 0.1733 1.0000
9.000 1.0266 0.02580 0.01726 -0.0268 0.1540 1.0000
9.250 1.0393 0.02685 0.01831 -0.0254 0.1350 1.0000
9.500 1.0506 0.02801 0.01945 -0.0239 0.1181 1.0000
9.750 1.0611 0.02927 0.02069 -0.0224 0.1031 1.0000
10.000 1.0711 0.03059 0.02203 -0.0210 0.0906 1.0000
10.250 1.0808 0.03199 0.02346 -0.0196 0.0799 1.0000
10.500 1.0890 0.03352 0.02501 -0.0181 0.0711 1.0000
10.750 1.0963 0.03516 0.02670 -0.0167 0.0644 1.0000
11.000 1.1043 0.03683 0.02851 -0.0154 0.0585 1.0000
11.250 1.1107 0.03859 0.03034 -0.0141 0.0532 1.0000
11.500 1.1167 0.04053 0.03238 -0.0129 0.0491 1.0000
11.750 1.1239 0.04242 0.03442 -0.0118 0.0452 1.0000
12.000 1.1281 0.04452 0.03659 -0.0108 0.0420 1.0000
12.250 1.1326 0.04679 0.03898 -0.0098 0.0391 1.0000
12.500 1.1385 0.04899 0.04140 -0.0089 0.0361 1.0000
12.750 1.1418 0.05136 0.04390 -0.0083 0.0337 1.0000
13.000 1.1418 0.05406 0.04666 -0.0078 0.0316 1.0000
13.250 1.1437 0.05690 0.04970 -0.0072 0.0297 1.0000
13.500 1.1448 0.05992 0.05298 -0.0068 0.0278 1.0000
13.750 1.1436 0.06312 0.05638 -0.0068 0.0262 1.0000
14.000 1.1401 0.06648 0.05993 -0.0071 0.0248 1.0000
14.250 1.1355 0.07013 0.06367 -0.0077 0.0236 1.0000
14.500 1.1292 0.07436 0.06802 -0.0084 0.0226 1.0000
14.750 1.1213 0.07909 0.07306 -0.0097 0.0219 1.0000
15.000 1.1107 0.08446 0.07872 -0.0114 0.0212 1.0000
15.250 1.0990 0.09025 0.08476 -0.0137 0.0208 1.0000
15.500 1.0851 0.09669 0.09145 -0.0167 0.0204 1.0000
15.750 1.0690 0.10390 0.09889 -0.0206 0.0200 1.0000
16.000 1.0516 0.11183 0.10705 -0.0251 0.0200 1.0000
16.250 1.0315 0.12090 0.11632 -0.0306 0.0202 1.0000
16.500 1.0090 0.13112 0.12673 -0.0371 0.0206 1.0000
16.750 0.9825 0.14323 0.13894 -0.0447 0.0212 1.0000
17.000 0.9558 0.15641 0.15220 -0.0528 0.0218 1.0000
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