MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 100,000 Max Cl/Cd: 40.4 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh84-il-100000.txt Download as CSV file: xf-mh84-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2615 0.12289 0.11846 -0.0041 1.0000 0.0893
-9.750 -0.2687 0.12140 0.11705 -0.0088 1.0000 0.0921
-9.500 -0.2716 0.11877 0.11452 -0.0126 1.0000 0.0929
-9.250 -0.2421 0.11341 0.10919 -0.0104 1.0000 0.0947
-9.000 -0.2282 0.11028 0.10613 -0.0112 1.0000 0.0971
-8.750 -0.2198 0.10740 0.10333 -0.0134 1.0000 0.1004
-8.500 -0.2371 0.10647 0.10256 -0.0214 1.0000 0.1036
-8.250 -0.2190 0.10177 0.09795 -0.0219 1.0000 0.1048
-8.000 -0.1955 0.09813 0.09438 -0.0215 1.0000 0.1072
-7.750 -0.1764 0.09493 0.09125 -0.0256 0.9760 0.1109
-7.500 -0.1763 0.09148 0.08779 -0.0427 0.9363 0.1166
-7.250 -0.1394 0.08660 0.08285 -0.0392 0.9181 0.1186
-7.000 -0.1244 0.08403 0.08021 -0.0384 0.8938 0.1215
-6.750 -0.1216 0.08191 0.07807 -0.0388 0.8701 0.1256
-6.500 -0.1485 0.07995 0.07611 -0.0500 0.8473 0.1303
-6.250 -0.1319 0.07693 0.07307 -0.0436 0.8321 0.1317
-6.000 -0.1173 0.07473 0.07081 -0.0402 0.8173 0.1347
-5.500 -0.1258 0.03981 0.03428 -0.0822 0.8012 0.0654
-5.250 -0.1047 0.03597 0.02993 -0.0838 0.7872 0.0653
-5.000 -0.0820 0.03267 0.02600 -0.0844 0.7751 0.0657
-4.750 -0.0587 0.03039 0.02346 -0.0839 0.7630 0.0666
-4.500 -0.0329 0.02857 0.02141 -0.0837 0.7495 0.0681
-4.250 -0.0072 0.02685 0.01928 -0.0829 0.7385 0.0705
-4.000 0.0198 0.02537 0.01748 -0.0825 0.7253 0.0753
-3.750 0.0473 0.02442 0.01625 -0.0818 0.7130 0.0824
-3.500 0.0733 0.02335 0.01512 -0.0808 0.7020 0.0907
-3.250 0.1010 0.02249 0.01424 -0.0805 0.6888 0.1055
-3.000 0.1278 0.02185 0.01352 -0.0795 0.6788 0.1291
-2.750 0.1555 0.02140 0.01319 -0.0792 0.6654 0.1623
-2.500 0.1828 0.02126 0.01304 -0.0786 0.6540 0.1965
-2.250 0.2095 0.02109 0.01290 -0.0779 0.6427 0.2264
-2.000 0.2372 0.02092 0.01269 -0.0775 0.6303 0.2557
-1.750 0.2639 0.02064 0.01237 -0.0765 0.6207 0.2822
-1.500 0.2918 0.02047 0.01221 -0.0762 0.6077 0.3096
-1.250 0.3192 0.02021 0.01184 -0.0755 0.5980 0.3371
-1.000 0.3466 0.01998 0.01171 -0.0750 0.5859 0.3647
-0.750 0.3742 0.01984 0.01150 -0.0745 0.5754 0.3964
-0.500 0.4013 0.01958 0.01133 -0.0738 0.5647 0.4293
-0.250 0.4283 0.01945 0.01130 -0.0732 0.5539 0.4688
0.000 0.4548 0.01918 0.01111 -0.0723 0.5442 0.5202
0.250 0.4805 0.01899 0.01121 -0.0714 0.5332 0.5928
0.500 0.5023 0.01847 0.01105 -0.0690 0.5247 0.7202
0.750 0.5318 0.01802 0.01091 -0.0683 0.5133 1.0000
1.000 0.5619 0.01821 0.01069 -0.0683 0.5046 1.0000
1.250 0.5905 0.01859 0.01094 -0.0685 0.4933 1.0000
1.500 0.6195 0.01880 0.01082 -0.0681 0.4853 1.0000
1.750 0.6473 0.01922 0.01118 -0.0682 0.4740 1.0000
2.000 0.6760 0.01945 0.01110 -0.0678 0.4664 1.0000
2.250 0.7033 0.01992 0.01156 -0.0678 0.4556 1.0000
2.500 0.7319 0.02016 0.01152 -0.0674 0.4482 1.0000
2.750 0.7587 0.02068 0.01206 -0.0674 0.4379 1.0000
3.000 0.7870 0.02096 0.01211 -0.0670 0.4306 1.0000
3.250 0.8136 0.02153 0.01268 -0.0669 0.4212 1.0000
3.500 0.8414 0.02184 0.01282 -0.0666 0.4136 1.0000
3.750 0.8680 0.02243 0.01336 -0.0664 0.4055 1.0000
4.000 0.8949 0.02287 0.01374 -0.0662 0.3976 1.0000
4.250 0.9227 0.02332 0.01400 -0.0659 0.3912 1.0000
4.500 0.9478 0.02398 0.01475 -0.0657 0.3825 1.0000
4.750 0.9757 0.02432 0.01491 -0.0654 0.3765 1.0000
5.000 1.0003 0.02514 0.01580 -0.0652 0.3690 1.0000
5.250 1.0264 0.02566 0.01627 -0.0649 0.3621 1.0000
5.500 1.0548 0.02611 0.01650 -0.0647 0.3569 1.0000
5.750 1.0767 0.02708 0.01770 -0.0644 0.3492 1.0000
6.000 1.1032 0.02758 0.01811 -0.0641 0.3434 1.0000
6.250 1.1296 0.02826 0.01868 -0.0638 0.3383 1.0000
6.500 1.1508 0.02930 0.01992 -0.0634 0.3313 1.0000
6.750 1.1769 0.02982 0.02037 -0.0631 0.3261 1.0000
7.000 1.2033 0.03056 0.02099 -0.0629 0.3216 1.0000
7.250 1.2212 0.03190 0.02260 -0.0624 0.3152 1.0000
7.500 1.2457 0.03255 0.02323 -0.0620 0.3101 1.0000
7.750 1.2749 0.03301 0.02348 -0.0618 0.3062 1.0000
8.000 1.2877 0.03485 0.02568 -0.0611 0.3006 1.0000
8.250 1.3074 0.03600 0.02693 -0.0606 0.2956 1.0000
8.500 1.3340 0.03649 0.02732 -0.0603 0.2916 1.0000
8.750 1.3550 0.03774 0.02860 -0.0598 0.2876 1.0000
9.000 1.3611 0.04003 0.03123 -0.0588 0.2825 1.0000
9.250 1.3791 0.04129 0.03256 -0.0582 0.2784 1.0000
9.500 1.4065 0.04178 0.03296 -0.0579 0.2750 1.0000
9.750 1.4216 0.04354 0.03481 -0.0573 0.2715 1.0000
10.000 1.4020 0.04772 0.03945 -0.0553 0.2671 1.0000
10.250 1.3988 0.05046 0.04236 -0.0540 0.2633 1.0000
10.500 1.4275 0.05075 0.04259 -0.0537 0.2601 1.0000
10.750 1.4728 0.05033 0.04199 -0.0542 0.2574 1.0000
11.000 0.8381 0.15131 0.14435 -0.0994 0.2920 1.0000
11.250 0.8706 0.15456 0.14761 -0.0984 0.2901 1.0000
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Polar data table (+)
Polar graphs
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