MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 50,000 Max Cl/Cd: 27.35 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh106-il-50000-n5.txt Download as CSV file: xf-mh106-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6789 0.09708 0.09009 -0.0086 1.0000 0.0334
-11.750 -0.6952 0.08959 0.08254 -0.0134 1.0000 0.0332
-11.500 -0.7098 0.08311 0.07598 -0.0176 1.0000 0.0329
-11.250 -0.7254 0.07712 0.06988 -0.0215 1.0000 0.0327
-11.000 -0.7432 0.07153 0.06413 -0.0247 1.0000 0.0325
-10.750 -0.7589 0.06688 0.05930 -0.0266 1.0000 0.0325
-10.500 -0.7733 0.06282 0.05503 -0.0271 1.0000 0.0325
-10.250 -0.7848 0.05925 0.05123 -0.0265 1.0000 0.0325
-10.000 -0.7930 0.05606 0.04777 -0.0249 1.0000 0.0327
-9.750 -0.7964 0.05301 0.04440 -0.0232 1.0000 0.0330
-9.500 -0.7935 0.04999 0.04110 -0.0217 1.0000 0.0336
-9.250 -0.7849 0.04732 0.03835 -0.0206 1.0000 0.0349
-9.000 -0.7753 0.04503 0.03593 -0.0194 1.0000 0.0369
-8.750 -0.7629 0.04275 0.03337 -0.0181 1.0000 0.0392
-8.500 -0.7466 0.04048 0.03080 -0.0168 1.0000 0.0415
-8.250 -0.7280 0.03835 0.02842 -0.0154 1.0000 0.0434
-8.000 -0.7143 0.03634 0.02645 -0.0140 1.0000 0.0466
-7.750 -0.6996 0.03463 0.02460 -0.0125 1.0000 0.0521
-7.500 -0.6863 0.03282 0.02273 -0.0107 1.0000 0.0573
-7.250 -0.6728 0.03115 0.02095 -0.0089 1.0000 0.0659
-7.000 -0.6611 0.02931 0.01916 -0.0070 1.0000 0.0788
-6.750 -0.6506 0.02728 0.01738 -0.0051 1.0000 0.1026
-6.500 -0.6419 0.02514 0.01591 -0.0031 1.0000 0.1663
-6.250 -0.6303 0.02407 0.01524 -0.0009 1.0000 0.2489
-6.000 -0.6168 0.02358 0.01483 0.0013 1.0000 0.3049
-5.750 -0.6035 0.02328 0.01461 0.0037 1.0000 0.3496
-5.500 -0.5883 0.02300 0.01439 0.0060 1.0000 0.3849
-5.250 -0.5705 0.02263 0.01399 0.0079 1.0000 0.4119
-5.000 -0.5515 0.02220 0.01346 0.0095 1.0000 0.4341
-4.750 -0.5324 0.02177 0.01301 0.0109 1.0000 0.4538
-4.500 -0.5143 0.02139 0.01262 0.0124 1.0000 0.4724
-4.250 -0.4858 0.02103 0.01217 0.0118 0.9861 0.4947
-4.000 -0.4394 0.02067 0.01171 0.0081 0.9550 0.5208
-3.750 -0.3940 0.02033 0.01129 0.0048 0.9251 0.5476
-3.500 -0.3509 0.02005 0.01092 0.0022 0.8963 0.5753
-3.250 -0.3130 0.01983 0.01059 0.0008 0.8677 0.6031
-3.000 -0.2805 0.01967 0.01034 0.0006 0.8401 0.6309
-2.750 -0.2513 0.01958 0.01016 0.0012 0.8146 0.6592
-2.500 -0.2231 0.01954 0.01003 0.0020 0.7918 0.6879
-2.250 -0.1952 0.01955 0.00994 0.0029 0.7696 0.7171
-2.000 -0.1661 0.01961 0.00990 0.0036 0.7501 0.7468
-1.750 -0.1350 0.01973 0.00991 0.0040 0.7314 0.7761
-1.500 -0.1015 0.01988 0.00993 0.0038 0.7134 0.8041
-1.250 -0.0656 0.02008 0.00998 0.0031 0.6966 0.8304
-1.000 -0.0287 0.02028 0.01002 0.0020 0.6811 0.8555
-0.750 0.0093 0.02049 0.01007 0.0006 0.6663 0.8792
-0.500 0.0517 0.02070 0.01012 -0.0017 0.6521 0.8997
-0.250 0.0954 0.02088 0.01014 -0.0046 0.6388 0.9189
0.000 0.1369 0.02103 0.01015 -0.0072 0.6265 0.9387
0.250 0.1811 0.02112 0.01010 -0.0105 0.6150 0.9566
0.500 0.2264 0.02118 0.01009 -0.0142 0.6031 0.9737
0.750 0.2722 0.02121 0.01005 -0.0183 0.5918 0.9904
1.000 0.3083 0.02123 0.01001 -0.0206 0.5824 1.0000
1.250 0.3278 0.02137 0.01010 -0.0197 0.5740 1.0000
1.500 0.3477 0.02156 0.01027 -0.0189 0.5657 1.0000
1.750 0.3684 0.02176 0.01041 -0.0180 0.5581 1.0000
2.000 0.3892 0.02205 0.01073 -0.0173 0.5500 1.0000
2.250 0.4101 0.02230 0.01094 -0.0164 0.5430 1.0000
2.500 0.4308 0.02266 0.01134 -0.0156 0.5349 1.0000
2.750 0.4519 0.02295 0.01163 -0.0146 0.5283 1.0000
3.000 0.4727 0.02338 0.01211 -0.0138 0.5202 1.0000
3.250 0.4940 0.02371 0.01243 -0.0128 0.5135 1.0000
3.500 0.5147 0.02421 0.01301 -0.0120 0.5055 1.0000
3.750 0.5361 0.02456 0.01338 -0.0109 0.4988 1.0000
4.000 0.5565 0.02511 0.01404 -0.0101 0.4905 1.0000
4.250 0.5783 0.02546 0.01440 -0.0090 0.4837 1.0000
4.500 0.5982 0.02608 0.01517 -0.0081 0.4750 1.0000
4.750 0.6204 0.02638 0.01547 -0.0069 0.4682 1.0000
5.000 0.6395 0.02707 0.01632 -0.0060 0.4587 1.0000
5.250 0.6611 0.02746 0.01676 -0.0048 0.4510 1.0000
5.500 0.6810 0.02801 0.01746 -0.0037 0.4417 1.0000
5.750 0.7005 0.02859 0.01818 -0.0026 0.4322 1.0000
6.000 0.7234 0.02878 0.01838 -0.0013 0.4241 1.0000
6.250 0.7412 0.02947 0.01927 -0.0001 0.4128 1.0000
6.500 0.7601 0.03001 0.01995 0.0012 0.4021 1.0000
6.750 0.7813 0.03029 0.02034 0.0025 0.3920 1.0000
7.000 0.8018 0.03057 0.02072 0.0039 0.3809 1.0000
7.250 0.8193 0.03113 0.02146 0.0053 0.3683 1.0000
7.500 0.8369 0.03162 0.02212 0.0068 0.3554 1.0000
7.750 0.8545 0.03205 0.02270 0.0083 0.3422 1.0000
8.000 0.8718 0.03245 0.02329 0.0098 0.3283 1.0000
8.250 0.8882 0.03286 0.02385 0.0115 0.3137 1.0000
8.500 0.9040 0.03327 0.02440 0.0131 0.2985 1.0000
8.750 0.9190 0.03371 0.02495 0.0148 0.2829 1.0000
9.000 0.9333 0.03413 0.02545 0.0166 0.2669 1.0000
9.250 0.9461 0.03470 0.02604 0.0185 0.2509 1.0000
9.500 0.9543 0.03570 0.02716 0.0204 0.2345 1.0000
9.750 0.9615 0.03681 0.02829 0.0223 0.2193 1.0000
10.000 0.9661 0.03809 0.02958 0.0243 0.2050 1.0000
10.250 0.9685 0.03954 0.03101 0.0262 0.1923 1.0000
10.500 0.9694 0.04101 0.03239 0.0284 0.1813 1.0000
10.750 0.9639 0.04325 0.03475 0.0299 0.1710 1.0000
11.000 0.9606 0.04559 0.03713 0.0308 0.1614 1.0000
11.250 0.9607 0.04775 0.03923 0.0315 0.1522 1.0000
11.500 0.9564 0.05067 0.04228 0.0315 0.1438 1.0000
11.750 0.9539 0.05352 0.04517 0.0314 0.1360 1.0000
12.000 0.9532 0.05619 0.04784 0.0314 0.1281 1.0000
12.250 0.9472 0.05986 0.05166 0.0306 0.1217 1.0000
12.500 0.9471 0.06267 0.05453 0.0303 0.1150 1.0000
12.750 0.9397 0.06675 0.05875 0.0292 0.1096 1.0000
13.000 0.9313 0.07106 0.06320 0.0277 0.1042 1.0000
13.250 0.9332 0.07381 0.06591 0.0274 0.0987 1.0000
13.500 0.9141 0.08033 0.07269 0.0244 0.0960 1.0000
13.750 0.8938 0.08734 0.07989 0.0211 0.0934 1.0000
14.000 0.9084 0.08775 0.08015 0.0221 0.0866 1.0000
14.250 0.8800 0.09670 0.08933 0.0175 0.0858 1.0000
14.500 0.8410 0.10874 0.10150 0.0109 0.0858 1.0000
14.750 0.7938 0.12425 0.11694 0.0026 0.0859 1.0000
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Polar data table (+)
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