MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 200,000 Max Cl/Cd: 61.77 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh46-il-200000.txt Download as CSV file: xf-mh46-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5399 0.11127 0.10784 0.0065 1.0000 0.0389
-9.750 -0.5392 0.10704 0.10364 0.0038 1.0000 0.0403
-9.500 -0.5442 0.10217 0.09883 -0.0017 1.0000 0.0420
-9.250 -0.4711 0.09023 0.08721 -0.0054 1.0000 0.0443
-9.000 -0.4653 0.08656 0.08355 -0.0055 1.0000 0.0453
-8.750 -0.4631 0.08251 0.07952 -0.0065 1.0000 0.0464
-8.500 -0.4638 0.07807 0.07510 -0.0081 1.0000 0.0474
-8.250 -0.4674 0.07326 0.07033 -0.0102 1.0000 0.0484
-8.000 -0.4737 0.06817 0.06527 -0.0130 1.0000 0.0492
-7.750 -0.4859 0.06250 0.05965 -0.0170 1.0000 0.0501
-7.500 -0.5030 0.05639 0.05355 -0.0221 1.0000 0.0502
-7.250 -0.5133 0.04996 0.04700 -0.0260 1.0000 0.0514
-6.250 -0.5407 0.03151 0.02596 -0.0260 1.0000 0.0222
-6.000 -0.5212 0.02887 0.02311 -0.0248 1.0000 0.0203
-5.750 -0.5059 0.02554 0.01938 -0.0230 1.0000 0.0194
-5.500 -0.4896 0.02301 0.01647 -0.0209 1.0000 0.0188
-5.250 -0.4746 0.02104 0.01422 -0.0185 1.0000 0.0186
-5.000 -0.4612 0.01951 0.01247 -0.0158 1.0000 0.0186
-4.750 -0.4485 0.01826 0.01103 -0.0131 1.0000 0.0190
-4.500 -0.4238 0.01699 0.00960 -0.0125 0.9972 0.0204
-4.250 -0.3864 0.01530 0.00785 -0.0147 0.9898 0.0250
-4.000 -0.3466 0.01393 0.00643 -0.0171 0.9830 0.0393
-3.750 -0.3123 0.01204 0.00525 -0.0190 0.9745 0.1653
-3.500 -0.2721 0.01126 0.00491 -0.0220 0.9682 0.2760
-3.250 -0.2368 0.01076 0.00462 -0.0237 0.9584 0.3572
-3.000 -0.2044 0.01028 0.00445 -0.0247 0.9481 0.4475
-2.750 -0.1748 0.00988 0.00431 -0.0248 0.9373 0.5300
-2.500 -0.1487 0.00953 0.00419 -0.0241 0.9258 0.6071
-2.250 -0.1257 0.00917 0.00410 -0.0224 0.9141 0.6887
-2.000 -0.1022 0.00882 0.00403 -0.0205 0.9018 0.7816
-1.750 -0.0555 0.00862 0.00400 -0.0233 0.8927 0.8861
-1.500 0.0030 0.00864 0.00392 -0.0287 0.8851 0.9420
-1.250 0.0533 0.00872 0.00384 -0.0328 0.8744 0.9721
-1.000 0.1057 0.00874 0.00371 -0.0377 0.8629 0.9952
-0.750 0.1351 0.00870 0.00354 -0.0381 0.8487 1.0000
-0.500 0.1556 0.00870 0.00340 -0.0365 0.8342 1.0000
-0.250 0.1770 0.00871 0.00330 -0.0351 0.8200 1.0000
0.000 0.1991 0.00874 0.00322 -0.0338 0.8059 1.0000
0.250 0.2217 0.00878 0.00316 -0.0325 0.7918 1.0000
0.500 0.2448 0.00882 0.00310 -0.0314 0.7776 1.0000
0.750 0.2683 0.00887 0.00306 -0.0303 0.7633 1.0000
1.000 0.2920 0.00893 0.00303 -0.0293 0.7487 1.0000
1.250 0.3161 0.00899 0.00302 -0.0283 0.7337 1.0000
1.500 0.3405 0.00905 0.00304 -0.0275 0.7176 1.0000
1.750 0.3650 0.00912 0.00305 -0.0266 0.7012 1.0000
2.000 0.3897 0.00920 0.00306 -0.0258 0.6845 1.0000
2.250 0.4144 0.00928 0.00308 -0.0249 0.6675 1.0000
2.500 0.4392 0.00938 0.00314 -0.0241 0.6502 1.0000
2.750 0.4642 0.00948 0.00321 -0.0234 0.6309 1.0000
3.000 0.4891 0.00960 0.00327 -0.0227 0.6119 1.0000
3.250 0.5141 0.00973 0.00337 -0.0219 0.5917 1.0000
3.500 0.5391 0.00988 0.00349 -0.0212 0.5709 1.0000
3.750 0.5641 0.01005 0.00362 -0.0206 0.5490 1.0000
4.000 0.5888 0.01026 0.00376 -0.0198 0.5270 1.0000
4.250 0.6137 0.01046 0.00394 -0.0192 0.5028 1.0000
4.500 0.6383 0.01070 0.00414 -0.0185 0.4784 1.0000
4.750 0.6628 0.01096 0.00439 -0.0178 0.4532 1.0000
5.000 0.6871 0.01125 0.00464 -0.0171 0.4264 1.0000
5.250 0.7112 0.01156 0.00491 -0.0164 0.3981 1.0000
5.500 0.7351 0.01190 0.00521 -0.0157 0.3680 1.0000
5.750 0.7585 0.01230 0.00554 -0.0150 0.3359 1.0000
6.000 0.7816 0.01274 0.00595 -0.0143 0.3014 1.0000
6.250 0.8042 0.01327 0.00638 -0.0135 0.2658 1.0000
6.500 0.8265 0.01384 0.00686 -0.0128 0.2285 1.0000
6.750 0.8481 0.01451 0.00742 -0.0120 0.1909 1.0000
7.000 0.8688 0.01531 0.00807 -0.0112 0.1528 1.0000
7.250 0.8882 0.01629 0.00886 -0.0102 0.1137 1.0000
7.500 0.9061 0.01751 0.00993 -0.0090 0.0816 1.0000
7.750 0.9227 0.01888 0.01126 -0.0075 0.0617 1.0000
8.000 0.9392 0.02022 0.01261 -0.0060 0.0499 1.0000
8.250 0.9546 0.02169 0.01408 -0.0044 0.0428 1.0000
8.500 0.9709 0.02324 0.01577 -0.0027 0.0382 1.0000
8.750 0.9880 0.02440 0.01698 -0.0015 0.0329 1.0000
9.000 1.0016 0.02707 0.01975 0.0003 0.0298 1.0000
9.250 1.0190 0.02811 0.02100 0.0017 0.0260 1.0000
9.500 1.0335 0.02968 0.02264 0.0031 0.0230 1.0000
9.750 1.0417 0.03391 0.02715 0.0049 0.0206 1.0000
10.000 1.0543 0.03441 0.02790 0.0066 0.0178 1.0000
10.250 1.0633 0.03654 0.03026 0.0084 0.0166 1.0000
10.500 1.0680 0.03879 0.03277 0.0103 0.0155 1.0000
10.750 1.0677 0.04137 0.03558 0.0127 0.0151 1.0000
11.000 1.0627 0.04400 0.03840 0.0150 0.0146 1.0000
11.250 1.0543 0.04712 0.04177 0.0168 0.0145 1.0000
11.500 1.0435 0.05057 0.04548 0.0178 0.0146 1.0000
11.750 1.0306 0.05443 0.04956 0.0179 0.0144 1.0000
12.000 1.0165 0.05872 0.05407 0.0171 0.0144 1.0000
12.250 0.9980 0.06407 0.05968 0.0150 0.0147 1.0000
12.500 0.9781 0.07021 0.06607 0.0117 0.0149 1.0000
12.750 0.9564 0.07740 0.07348 0.0073 0.0152 1.0000
13.000 0.9355 0.08508 0.08132 0.0021 0.0151 1.0000
13.250 0.8937 0.09904 0.09550 -0.0078 0.0165 1.0000
13.500 0.8554 0.11427 0.11084 -0.0174 0.0179 1.0000
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Polar data table (+)
Polar graphs
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