MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 500,000 Max Cl/Cd: 86.64 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh106-il-500000.txt Download as CSV file: xf-mh106-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6915 0.07275 0.07020 -0.0142 1.0000 0.0098
-12.250 -0.7110 0.06497 0.06231 -0.0185 1.0000 0.0097
-12.000 -0.7332 0.05721 0.05441 -0.0226 1.0000 0.0096
-11.750 -0.7584 0.04973 0.04679 -0.0263 1.0000 0.0096
-11.500 -0.7784 0.04402 0.04092 -0.0287 1.0000 0.0095
-11.250 -0.8563 0.04886 0.04539 -0.0308 1.0000 0.0098
-11.000 -0.8766 0.04481 0.04115 -0.0296 1.0000 0.0095
-10.750 -0.8914 0.04174 0.03790 -0.0270 1.0000 0.0092
-10.500 -0.9395 0.03418 0.02943 -0.0194 1.0000 0.0076
-10.250 -0.9360 0.03189 0.02690 -0.0168 1.0000 0.0075
-10.000 -0.9281 0.02975 0.02455 -0.0146 1.0000 0.0076
-9.750 -0.9173 0.02776 0.02235 -0.0127 1.0000 0.0076
-9.500 -0.9044 0.02595 0.02042 -0.0109 1.0000 0.0078
-9.250 -0.8892 0.02449 0.01883 -0.0093 1.0000 0.0079
-9.000 -0.8729 0.02319 0.01745 -0.0078 1.0000 0.0081
-8.750 -0.8554 0.02209 0.01626 -0.0064 1.0000 0.0084
-8.500 -0.8374 0.02101 0.01510 -0.0050 1.0000 0.0086
-8.250 -0.8188 0.02004 0.01405 -0.0036 1.0000 0.0089
-8.000 -0.8007 0.01899 0.01292 -0.0020 1.0000 0.0091
-7.750 -0.7823 0.01805 0.01189 -0.0004 1.0000 0.0093
-7.500 -0.7632 0.01722 0.01100 0.0011 1.0000 0.0096
-7.250 -0.7419 0.01667 0.01039 0.0022 1.0000 0.0101
-7.000 -0.7272 0.01548 0.00915 0.0044 1.0000 0.0109
-6.750 -0.7080 0.01481 0.00845 0.0059 1.0000 0.0116
-6.500 -0.6882 0.01422 0.00784 0.0074 1.0000 0.0124
-6.250 -0.6604 0.01358 0.00713 0.0072 0.9926 0.0134
-6.000 -0.6210 0.01264 0.00612 0.0046 0.9590 0.0165
-5.750 -0.5822 0.01173 0.00517 0.0023 0.9071 0.0320
-5.500 -0.5647 0.01076 0.00445 0.0042 0.8566 0.1000
-5.250 -0.5467 0.01002 0.00399 0.0059 0.8190 0.1815
-5.000 -0.5244 0.00968 0.00372 0.0070 0.7879 0.2314
-4.750 -0.5006 0.00946 0.00352 0.0079 0.7611 0.2650
-4.500 -0.4759 0.00929 0.00334 0.0086 0.7366 0.2946
-4.250 -0.4508 0.00914 0.00318 0.0092 0.7141 0.3217
-4.000 -0.4252 0.00903 0.00302 0.0097 0.6924 0.3428
-3.750 -0.3995 0.00891 0.00288 0.0102 0.6723 0.3665
-3.500 -0.3736 0.00880 0.00275 0.0107 0.6532 0.3899
-3.250 -0.3474 0.00871 0.00262 0.0111 0.6355 0.4081
-3.000 -0.3212 0.00861 0.00248 0.0115 0.6189 0.4260
-2.750 -0.2949 0.00852 0.00237 0.0119 0.6031 0.4450
-2.500 -0.2685 0.00845 0.00226 0.0123 0.5879 0.4653
-2.250 -0.2423 0.00835 0.00217 0.0127 0.5734 0.4863
-2.000 -0.2160 0.00826 0.00208 0.0131 0.5597 0.5101
-1.750 -0.1900 0.00815 0.00201 0.0136 0.5473 0.5356
-1.500 -0.1640 0.00806 0.00195 0.0141 0.5359 0.5635
-1.250 -0.1382 0.00797 0.00190 0.0146 0.5252 0.5937
-1.000 -0.1125 0.00787 0.00187 0.0151 0.5147 0.6258
-0.750 -0.0868 0.00778 0.00185 0.0157 0.5051 0.6593
-0.500 -0.0614 0.00771 0.00184 0.0163 0.4966 0.6925
-0.250 -0.0357 0.00762 0.00185 0.0170 0.4883 0.7267
0.000 -0.0100 0.00758 0.00187 0.0176 0.4810 0.7597
0.250 0.0161 0.00752 0.00189 0.0182 0.4734 0.7921
0.500 0.0423 0.00751 0.00194 0.0188 0.4669 0.8231
0.750 0.0697 0.00749 0.00200 0.0192 0.4603 0.8523
1.000 0.0983 0.00755 0.00208 0.0193 0.4542 0.8789
1.250 0.1296 0.00760 0.00218 0.0188 0.4482 0.9009
1.500 0.1630 0.00771 0.00228 0.0179 0.4422 0.9188
1.750 0.1980 0.00786 0.00240 0.0166 0.4365 0.9326
2.000 0.2332 0.00798 0.00252 0.0152 0.4307 0.9437
2.250 0.2655 0.00815 0.00263 0.0144 0.4253 0.9545
2.500 0.3061 0.00829 0.00278 0.0119 0.4194 0.9589
2.750 0.3432 0.00843 0.00290 0.0100 0.4139 0.9650
3.000 0.3795 0.00862 0.00303 0.0083 0.4085 0.9704
3.250 0.4197 0.00870 0.00314 0.0058 0.4026 0.9742
3.500 0.4560 0.00884 0.00325 0.0040 0.3969 0.9797
3.750 0.4941 0.00895 0.00337 0.0019 0.3908 0.9836
4.000 0.5341 0.00901 0.00344 -0.0007 0.3842 0.9870
4.250 0.5722 0.00913 0.00353 -0.0029 0.3780 0.9911
4.500 0.6110 0.00917 0.00362 -0.0053 0.3712 0.9946
4.750 0.6510 0.00925 0.00368 -0.0080 0.3642 0.9980
5.000 0.6854 0.00926 0.00374 -0.0095 0.3571 1.0000
5.250 0.7084 0.00937 0.00383 -0.0086 0.3507 1.0000
5.500 0.7322 0.00938 0.00392 -0.0079 0.3437 1.0000
5.750 0.7553 0.00950 0.00401 -0.0070 0.3362 1.0000
6.000 0.7791 0.00954 0.00412 -0.0063 0.3275 1.0000
6.250 0.8025 0.00965 0.00425 -0.0055 0.3180 1.0000
6.500 0.8258 0.00979 0.00438 -0.0047 0.3077 1.0000
6.750 0.8493 0.00991 0.00453 -0.0039 0.2949 1.0000
7.000 0.8723 0.01010 0.00470 -0.0031 0.2794 1.0000
7.250 0.8950 0.01033 0.00492 -0.0022 0.2604 1.0000
7.500 0.9165 0.01068 0.00520 -0.0012 0.2380 1.0000
7.750 0.9375 0.01110 0.00554 -0.0002 0.2146 1.0000
8.000 0.9576 0.01161 0.00595 0.0010 0.1910 1.0000
8.250 0.9773 0.01214 0.00640 0.0022 0.1695 1.0000
8.500 0.9969 0.01267 0.00687 0.0034 0.1510 1.0000
8.750 1.0163 0.01322 0.00738 0.0046 0.1337 1.0000
9.000 1.0350 0.01379 0.00790 0.0059 0.1179 1.0000
9.250 1.0534 0.01439 0.00845 0.0072 0.1039 1.0000
9.500 1.0716 0.01497 0.00901 0.0086 0.0918 1.0000
9.750 1.0895 0.01556 0.00959 0.0100 0.0813 1.0000
10.000 1.1065 0.01620 0.01021 0.0114 0.0716 1.0000
10.250 1.1220 0.01692 0.01091 0.0131 0.0623 1.0000
10.500 1.1382 0.01755 0.01155 0.0146 0.0550 1.0000
10.750 1.1530 0.01825 0.01227 0.0163 0.0480 1.0000
11.000 1.1637 0.01916 0.01315 0.0184 0.0410 1.0000
11.250 1.1776 0.01982 0.01385 0.0201 0.0362 1.0000
11.500 1.1850 0.02081 0.01484 0.0225 0.0313 1.0000
11.750 1.1924 0.02161 0.01570 0.0251 0.0279 1.0000
12.000 1.1881 0.02288 0.01698 0.0287 0.0245 1.0000
12.250 1.1925 0.02399 0.01817 0.0307 0.0222 1.0000
12.500 1.1929 0.02566 0.01990 0.0321 0.0199 1.0000
12.750 1.1882 0.02817 0.02248 0.0326 0.0178 1.0000
13.000 1.1901 0.03043 0.02486 0.0326 0.0165 1.0000
13.250 1.1892 0.03317 0.02766 0.0321 0.0148 1.0000
13.500 1.1820 0.03678 0.03135 0.0312 0.0137 1.0000
13.750 1.1776 0.04017 0.03485 0.0303 0.0126 1.0000
14.000 1.1736 0.04355 0.03834 0.0293 0.0120 1.0000
14.250 1.1700 0.04690 0.04178 0.0283 0.0113 1.0000
14.500 1.1619 0.05086 0.04583 0.0271 0.0107 1.0000
14.750 1.1518 0.05508 0.05012 0.0257 0.0101 1.0000
15.000 1.1356 0.06015 0.05529 0.0240 0.0097 1.0000
15.250 1.1249 0.06465 0.05989 0.0224 0.0093 1.0000
15.500 1.1188 0.06872 0.06407 0.0209 0.0090 1.0000
15.750 1.1111 0.07311 0.06855 0.0193 0.0086 1.0000
16.000 1.1036 0.07759 0.07313 0.0175 0.0083 1.0000
16.250 1.0993 0.08167 0.07729 0.0159 0.0080 1.0000
16.500 1.0876 0.08695 0.08265 0.0137 0.0077 1.0000
16.750 1.0768 0.09224 0.08802 0.0115 0.0073 1.0000
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Polar data table (+)
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