MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 100,000 Max Cl/Cd: 42.15 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh108-il-100000-n5.txt Download as CSV file: xf-mh108-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7964 0.08246 0.07720 -0.0046 1.0000 0.0173
-12.250 -0.8175 0.07404 0.06865 -0.0107 1.0000 0.0171
-12.000 -0.8366 0.06675 0.06119 -0.0160 1.0000 0.0170
-11.750 -0.8553 0.06044 0.05468 -0.0203 1.0000 0.0169
-11.500 -0.8707 0.05551 0.04952 -0.0229 1.0000 0.0170
-11.250 -0.8850 0.05135 0.04512 -0.0237 1.0000 0.0170
-11.000 -0.8964 0.04794 0.04143 -0.0231 1.0000 0.0173
-10.750 -0.9037 0.04515 0.03845 -0.0215 1.0000 0.0177
-10.500 -0.9060 0.04308 0.03630 -0.0195 1.0000 0.0182
-10.250 -0.9040 0.04115 0.03425 -0.0176 1.0000 0.0188
-10.000 -0.8984 0.03927 0.03219 -0.0159 1.0000 0.0198
-9.750 -0.8903 0.03725 0.02994 -0.0142 1.0000 0.0209
-9.500 -0.8801 0.03513 0.02750 -0.0125 1.0000 0.0222
-9.250 -0.8679 0.03307 0.02518 -0.0108 1.0000 0.0233
-9.000 -0.8559 0.03130 0.02335 -0.0093 1.0000 0.0246
-8.750 -0.8408 0.02987 0.02182 -0.0079 1.0000 0.0269
-8.500 -0.8236 0.02849 0.02020 -0.0065 1.0000 0.0303
-8.250 -0.8084 0.02705 0.01877 -0.0051 1.0000 0.0338
-8.000 -0.7902 0.02578 0.01730 -0.0036 1.0000 0.0391
-7.750 -0.7726 0.02458 0.01613 -0.0024 1.0000 0.0460
-7.500 -0.7537 0.02347 0.01496 -0.0012 1.0000 0.0548
-7.250 -0.7337 0.02250 0.01397 -0.0001 1.0000 0.0658
-7.000 -0.7129 0.02165 0.01311 0.0010 1.0000 0.0785
-6.750 -0.6917 0.02088 0.01233 0.0019 1.0000 0.0922
-6.500 -0.6701 0.02017 0.01161 0.0029 1.0000 0.1065
-6.250 -0.6483 0.01949 0.01093 0.0039 1.0000 0.1212
-6.000 -0.6263 0.01887 0.01029 0.0048 1.0000 0.1369
-5.750 -0.6040 0.01829 0.00971 0.0058 1.0000 0.1542
-5.500 -0.5819 0.01774 0.00919 0.0068 1.0000 0.1717
-5.250 -0.5601 0.01720 0.00873 0.0078 1.0000 0.1908
-5.000 -0.5382 0.01672 0.00829 0.0088 1.0000 0.2115
-4.750 -0.5169 0.01626 0.00790 0.0099 1.0000 0.2337
-4.500 -0.4959 0.01585 0.00756 0.0110 1.0000 0.2572
-4.250 -0.4584 0.01538 0.00720 0.0088 0.9649 0.2899
-4.000 -0.4179 0.01496 0.00686 0.0062 0.9216 0.3274
-3.750 -0.3805 0.01461 0.00653 0.0045 0.8806 0.3661
-3.500 -0.3508 0.01435 0.00627 0.0046 0.8415 0.4038
-3.250 -0.3255 0.01413 0.00605 0.0055 0.8069 0.4405
-3.000 -0.3016 0.01394 0.00583 0.0068 0.7761 0.4790
-2.750 -0.2780 0.01374 0.00566 0.0081 0.7481 0.5186
-2.500 -0.2541 0.01356 0.00552 0.0094 0.7220 0.5607
-2.250 -0.2296 0.01340 0.00540 0.0106 0.6981 0.6054
-2.000 -0.2041 0.01327 0.00530 0.0117 0.6758 0.6516
-1.750 -0.1773 0.01318 0.00525 0.0126 0.6545 0.6984
-1.500 -0.1488 0.01315 0.00523 0.0132 0.6339 0.7439
-1.250 -0.1173 0.01319 0.00523 0.0133 0.6145 0.7861
-1.000 -0.0835 0.01328 0.00527 0.0128 0.5952 0.8233
-0.750 -0.0472 0.01342 0.00531 0.0118 0.5764 0.8543
-0.500 -0.0113 0.01359 0.00535 0.0108 0.5588 0.8808
-0.250 0.0275 0.01378 0.00539 0.0091 0.5417 0.9017
0.000 0.0648 0.01397 0.00543 0.0076 0.5258 0.9207
0.250 0.1036 0.01415 0.00547 0.0058 0.5105 0.9367
0.500 0.1431 0.01432 0.00550 0.0036 0.4957 0.9507
0.750 0.1832 0.01446 0.00552 0.0013 0.4818 0.9637
1.000 0.2235 0.01458 0.00552 -0.0013 0.4686 0.9756
1.250 0.2642 0.01467 0.00552 -0.0040 0.4559 0.9864
1.500 0.3058 0.01473 0.00549 -0.0069 0.4443 0.9964
1.750 0.3357 0.01482 0.00546 -0.0076 0.4351 1.0000
2.000 0.3582 0.01493 0.00555 -0.0068 0.4256 1.0000
2.250 0.3807 0.01506 0.00562 -0.0060 0.4176 1.0000
2.500 0.4035 0.01521 0.00573 -0.0051 0.4093 1.0000
2.750 0.4264 0.01539 0.00587 -0.0043 0.4018 1.0000
3.000 0.4494 0.01557 0.00602 -0.0035 0.3942 1.0000
3.250 0.4725 0.01577 0.00621 -0.0027 0.3868 1.0000
3.500 0.4956 0.01599 0.00640 -0.0018 0.3796 1.0000
3.750 0.5189 0.01622 0.00664 -0.0010 0.3727 1.0000
4.000 0.5422 0.01645 0.00688 -0.0002 0.3654 1.0000
4.250 0.5655 0.01671 0.00714 0.0006 0.3588 1.0000
4.500 0.5888 0.01697 0.00744 0.0014 0.3514 1.0000
4.750 0.6121 0.01725 0.00772 0.0022 0.3450 1.0000
5.000 0.6354 0.01753 0.00806 0.0030 0.3374 1.0000
5.250 0.6587 0.01782 0.00835 0.0038 0.3311 1.0000
5.500 0.6819 0.01812 0.00876 0.0046 0.3232 1.0000
5.750 0.7051 0.01843 0.00906 0.0054 0.3169 1.0000
6.000 0.7281 0.01875 0.00950 0.0062 0.3088 1.0000
6.250 0.7511 0.01908 0.00984 0.0071 0.3021 1.0000
6.500 0.7739 0.01942 0.01032 0.0079 0.2937 1.0000
6.750 0.7965 0.01976 0.01072 0.0088 0.2864 1.0000
7.000 0.8190 0.02011 0.01118 0.0096 0.2779 1.0000
7.250 0.8412 0.02048 0.01165 0.0105 0.2696 1.0000
7.500 0.8633 0.02082 0.01207 0.0114 0.2613 1.0000
7.750 0.8849 0.02124 0.01265 0.0124 0.2518 1.0000
8.000 0.9064 0.02162 0.01311 0.0133 0.2430 1.0000
8.250 0.9274 0.02203 0.01362 0.0143 0.2332 1.0000
8.500 0.9480 0.02249 0.01424 0.0153 0.2226 1.0000
8.750 0.9681 0.02297 0.01485 0.0164 0.2125 1.0000
9.000 0.9875 0.02347 0.01540 0.0175 0.2021 1.0000
9.250 1.0063 0.02404 0.01610 0.0186 0.1909 1.0000
9.500 1.0242 0.02470 0.01687 0.0197 0.1794 1.0000
9.750 1.0410 0.02544 0.01770 0.0210 0.1681 1.0000
10.000 1.0563 0.02627 0.01859 0.0223 0.1575 1.0000
10.250 1.0696 0.02720 0.01955 0.0237 0.1472 1.0000
10.500 1.0817 0.02823 0.02072 0.0251 0.1369 1.0000
10.750 1.0920 0.02938 0.02198 0.0266 0.1270 1.0000
11.000 1.0988 0.03067 0.02332 0.0283 0.1184 1.0000
11.250 1.1026 0.03208 0.02483 0.0301 0.1102 1.0000
11.500 1.1016 0.03364 0.02648 0.0323 0.1034 1.0000
11.750 1.0966 0.03560 0.02852 0.0339 0.0976 1.0000
12.000 1.0914 0.03805 0.03105 0.0344 0.0923 1.0000
12.250 1.0854 0.04099 0.03413 0.0340 0.0870 1.0000
12.500 1.0759 0.04460 0.03776 0.0329 0.0831 1.0000
12.750 1.0694 0.04823 0.04155 0.0316 0.0786 1.0000
13.000 1.0597 0.05242 0.04585 0.0298 0.0745 1.0000
13.250 1.0479 0.05695 0.05040 0.0278 0.0713 1.0000
13.500 1.0381 0.06142 0.05497 0.0259 0.0678 1.0000
13.750 1.0274 0.06615 0.05982 0.0238 0.0643 1.0000
14.000 1.0159 0.07103 0.06476 0.0216 0.0615 1.0000
14.250 1.0054 0.07569 0.06939 0.0195 0.0589 1.0000
14.500 0.9955 0.08064 0.07450 0.0173 0.0560 1.0000
14.750 0.9852 0.08584 0.07981 0.0149 0.0530 1.0000
15.000 0.9754 0.09108 0.08510 0.0124 0.0504 1.0000
15.250 0.9688 0.09564 0.08962 0.0103 0.0479 1.0000
15.500 0.9584 0.10141 0.09557 0.0076 0.0457 1.0000
15.750 0.9483 0.10722 0.10151 0.0048 0.0435 1.0000
16.000 0.9390 0.11296 0.10732 0.0020 0.0412 1.0000
16.250 0.9333 0.11794 0.11229 -0.0005 0.0390 1.0000
16.500 0.9261 0.12339 0.11778 -0.0031 0.0373 1.0000
16.750 0.9116 0.13086 0.12543 -0.0069 0.0361 1.0000
17.000 0.8942 0.13929 0.13400 -0.0112 0.0351 1.0000
17.250 0.8614 0.15228 0.14711 -0.0179 0.0346 1.0000
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Polar data table (+)
Polar graphs
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