MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 500,000 Max Cl/Cd: 79.7 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh106-il-500000-n5.txt Download as CSV file: xf-mh106-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8293 0.12026 0.11755 0.0152 1.0000 0.0033
-15.500 -0.8447 0.11159 0.10875 0.0104 1.0000 0.0032
-15.250 -0.8684 0.10154 0.09855 0.0047 1.0000 0.0032
-15.000 -0.8935 0.09186 0.08872 -0.0010 1.0000 0.0033
-14.750 -0.8969 0.08684 0.08361 -0.0039 1.0000 0.0032
-14.500 -0.9160 0.07917 0.07581 -0.0084 1.0000 0.0032
-14.250 -0.9298 0.07261 0.06911 -0.0123 1.0000 0.0032
-14.000 -0.9469 0.06589 0.06224 -0.0162 1.0000 0.0032
-13.750 -0.9589 0.06014 0.05635 -0.0196 1.0000 0.0031
-13.500 -0.9704 0.05467 0.05071 -0.0228 1.0000 0.0032
-13.250 -0.9806 0.04983 0.04573 -0.0253 1.0000 0.0031
-13.000 -0.9889 0.04554 0.04126 -0.0273 1.0000 0.0032
-12.750 -0.9936 0.04210 0.03768 -0.0284 1.0000 0.0032
-12.500 -1.0081 0.03794 0.03332 -0.0288 1.0000 0.0033
-12.250 -1.0025 0.03624 0.03152 -0.0285 1.0000 0.0032
-12.000 -1.0126 0.03324 0.02832 -0.0272 1.0000 0.0032
-11.750 -1.0193 0.03087 0.02579 -0.0251 1.0000 0.0034
-11.500 -1.0168 0.02939 0.02420 -0.0230 1.0000 0.0034
-11.250 -1.0123 0.02815 0.02287 -0.0208 1.0000 0.0035
-11.000 -1.0073 0.02697 0.02160 -0.0182 1.0000 0.0036
-10.750 -1.0014 0.02586 0.02039 -0.0154 1.0000 0.0037
-10.500 -0.9919 0.02480 0.01922 -0.0131 1.0000 0.0037
-10.250 -0.9791 0.02381 0.01815 -0.0112 1.0000 0.0038
-10.000 -0.9651 0.02284 0.01709 -0.0094 1.0000 0.0039
-9.750 -0.9499 0.02191 0.01606 -0.0078 1.0000 0.0040
-9.500 -0.9337 0.02102 0.01508 -0.0062 1.0000 0.0041
-9.250 -0.9166 0.02017 0.01413 -0.0047 1.0000 0.0042
-9.000 -0.8990 0.01934 0.01322 -0.0032 1.0000 0.0044
-8.750 -0.8804 0.01858 0.01238 -0.0018 1.0000 0.0045
-8.500 -0.8611 0.01787 0.01160 -0.0005 1.0000 0.0046
-8.250 -0.8406 0.01726 0.01092 0.0006 1.0000 0.0048
-8.000 -0.8202 0.01664 0.01024 0.0018 1.0000 0.0049
-7.750 -0.7998 0.01587 0.00940 0.0029 0.9971 0.0053
-7.500 -0.7559 0.01519 0.00864 -0.0008 0.9260 0.0059
-7.250 -0.7296 0.01483 0.00808 -0.0005 0.8605 0.0064
-7.000 -0.7088 0.01449 0.00752 0.0010 0.8184 0.0069
-6.750 -0.6866 0.01416 0.00702 0.0022 0.7851 0.0073
-6.500 -0.6645 0.01373 0.00643 0.0033 0.7561 0.0082
-6.250 -0.6409 0.01341 0.00597 0.0041 0.7313 0.0094
-6.000 -0.6169 0.01307 0.00552 0.0049 0.7094 0.0115
-5.750 -0.5927 0.01274 0.00511 0.0056 0.6894 0.0157
-5.500 -0.5684 0.01240 0.00473 0.0063 0.6699 0.0253
-5.250 -0.5447 0.01197 0.00433 0.0070 0.6511 0.0441
-5.000 -0.5220 0.01140 0.00389 0.0078 0.6341 0.0835
-4.750 -0.4997 0.01078 0.00349 0.0086 0.6186 0.1421
-4.500 -0.4764 0.01029 0.00320 0.0093 0.6041 0.1976
-4.250 -0.4516 0.00997 0.00299 0.0098 0.5900 0.2385
-4.000 -0.4257 0.00979 0.00281 0.0102 0.5758 0.2634
-3.750 -0.3999 0.00959 0.00266 0.0106 0.5620 0.2925
-3.500 -0.3737 0.00944 0.00252 0.0110 0.5492 0.3183
-3.250 -0.3470 0.00933 0.00240 0.0113 0.5376 0.3343
-2.750 -0.2931 0.00916 0.00216 0.0118 0.5160 0.3627
-2.500 -0.2661 0.00908 0.00206 0.0120 0.5058 0.3772
-2.250 -0.2391 0.00901 0.00197 0.0123 0.4957 0.3914
-2.000 -0.2121 0.00894 0.00189 0.0125 0.4860 0.4067
-1.500 -0.1580 0.00880 0.00175 0.0130 0.4697 0.4389
-1.250 -0.1310 0.00873 0.00170 0.0132 0.4625 0.4563
-1.000 -0.1040 0.00867 0.00165 0.0135 0.4551 0.4753
-0.750 -0.0770 0.00860 0.00161 0.0137 0.4481 0.4957
-0.500 -0.0503 0.00853 0.00158 0.0140 0.4413 0.5174
-0.250 -0.0236 0.00846 0.00156 0.0143 0.4357 0.5418
0.000 0.0031 0.00838 0.00156 0.0146 0.4299 0.5669
0.250 0.0294 0.00833 0.00155 0.0150 0.4243 0.5942
0.500 0.0559 0.00825 0.00156 0.0153 0.4189 0.6227
0.750 0.0822 0.00818 0.00158 0.0158 0.4138 0.6519
1.000 0.1082 0.00813 0.00160 0.0162 0.4091 0.6824
1.250 0.1344 0.00806 0.00164 0.0167 0.4044 0.7127
1.500 0.1605 0.00801 0.00169 0.0172 0.3996 0.7433
1.750 0.1865 0.00798 0.00174 0.0177 0.3951 0.7748
2.000 0.2130 0.00793 0.00181 0.0182 0.3907 0.8055
2.250 0.2399 0.00791 0.00189 0.0186 0.3858 0.8353
2.500 0.2679 0.00793 0.00198 0.0187 0.3810 0.8631
2.750 0.2983 0.00797 0.00209 0.0184 0.3764 0.8880
3.000 0.3311 0.00804 0.00220 0.0175 0.3713 0.9089
3.250 0.3656 0.00816 0.00233 0.0162 0.3661 0.9247
3.500 0.4021 0.00826 0.00246 0.0144 0.3608 0.9363
3.750 0.4377 0.00837 0.00257 0.0128 0.3547 0.9454
4.000 0.4695 0.00850 0.00270 0.0120 0.3490 0.9546
4.250 0.5061 0.00861 0.00282 0.0102 0.3421 0.9596
4.500 0.5368 0.00875 0.00295 0.0096 0.3357 0.9671
4.750 0.5713 0.00886 0.00309 0.0082 0.3281 0.9716
5.000 0.6055 0.00900 0.00323 0.0068 0.3204 0.9766
5.250 0.6372 0.00914 0.00338 0.0060 0.3115 0.9823
5.500 0.6749 0.00928 0.00353 0.0039 0.3008 0.9856
5.750 0.7108 0.00944 0.00369 0.0020 0.2884 0.9896
6.000 0.7443 0.00965 0.00386 0.0007 0.2723 0.9933
6.250 0.7787 0.00990 0.00406 -0.0010 0.2518 0.9958
6.500 0.8121 0.01019 0.00429 -0.0024 0.2302 0.9984
6.750 0.8424 0.01057 0.00459 -0.0033 0.2085 1.0000
7.000 0.8638 0.01094 0.00490 -0.0023 0.1887 1.0000
7.250 0.8848 0.01135 0.00525 -0.0013 0.1704 1.0000
7.500 0.9056 0.01179 0.00562 -0.0002 0.1533 1.0000
7.750 0.9264 0.01221 0.00600 0.0009 0.1382 1.0000
8.000 0.9467 0.01266 0.00641 0.0020 0.1228 1.0000
8.250 0.9669 0.01313 0.00684 0.0031 0.1098 1.0000
8.500 0.9869 0.01360 0.00728 0.0043 0.0986 1.0000
8.750 1.0065 0.01408 0.00776 0.0055 0.0881 1.0000
9.000 1.0260 0.01457 0.00823 0.0067 0.0781 1.0000
9.250 1.0449 0.01509 0.00874 0.0080 0.0687 1.0000
9.500 1.0631 0.01565 0.00928 0.0093 0.0602 1.0000
9.750 1.0807 0.01623 0.00985 0.0107 0.0526 1.0000
10.000 1.0985 0.01678 0.01042 0.0121 0.0464 1.0000
10.250 1.1145 0.01744 0.01108 0.0136 0.0401 1.0000
10.500 1.1306 0.01806 0.01172 0.0152 0.0350 1.0000
10.750 1.1449 0.01876 0.01243 0.0169 0.0302 1.0000
11.000 1.1579 0.01950 0.01318 0.0187 0.0258 1.0000
11.250 1.1698 0.02026 0.01397 0.0207 0.0224 1.0000
11.500 1.1792 0.02111 0.01484 0.0228 0.0192 1.0000
11.750 1.1841 0.02195 0.01573 0.0257 0.0172 1.0000
12.000 1.1865 0.02293 0.01676 0.0285 0.0152 1.0000
12.250 1.1873 0.02427 0.01814 0.0307 0.0134 1.0000
12.500 1.1909 0.02574 0.01971 0.0319 0.0121 1.0000
12.750 1.1935 0.02758 0.02162 0.0324 0.0108 1.0000
13.000 1.1955 0.02975 0.02388 0.0325 0.0100 1.0000
13.250 1.1968 0.03219 0.02640 0.0322 0.0092 1.0000
13.500 1.1981 0.03475 0.02906 0.0317 0.0084 1.0000
13.750 1.1973 0.03765 0.03203 0.0309 0.0076 1.0000
14.000 1.1955 0.04071 0.03519 0.0301 0.0073 1.0000
14.250 1.1916 0.04405 0.03861 0.0292 0.0068 1.0000
14.500 1.1875 0.04747 0.04212 0.0282 0.0065 1.0000
14.750 1.1842 0.05081 0.04556 0.0272 0.0061 1.0000
15.000 1.1785 0.05447 0.04933 0.0260 0.0058 1.0000
15.250 1.1714 0.05836 0.05331 0.0247 0.0055 1.0000
15.500 1.1646 0.06226 0.05731 0.0234 0.0053 1.0000
15.750 1.1566 0.06652 0.06165 0.0218 0.0051 1.0000
16.000 1.1477 0.07101 0.06623 0.0201 0.0049 1.0000
16.250 1.1404 0.07538 0.07069 0.0184 0.0047 1.0000
16.500 1.1300 0.08034 0.07575 0.0164 0.0045 1.0000
16.750 1.1215 0.08507 0.08059 0.0144 0.0043 1.0000
17.000 1.1112 0.09024 0.08587 0.0123 0.0041 1.0000
17.250 1.1030 0.09514 0.09087 0.0102 0.0041 1.0000
17.500 1.0928 0.10046 0.09630 0.0078 0.0038 1.0000
17.750 1.0837 0.10573 0.10168 0.0055 0.0039 1.0000
18.000 1.0711 0.11173 0.10778 0.0027 0.0037 1.0000
18.250 1.0601 0.11755 0.11370 0.0000 0.0038 1.0000
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Polar data table (+)
Polar graphs
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