MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 50,000 Max Cl/Cd: 38.4 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh117-il-50000-n5.txt Download as CSV file: xf-mh117-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4294 0.09827 0.09121 -0.0314 1.0000 0.0419
-9.250 -0.4311 0.09396 0.08699 -0.0333 1.0000 0.0422
-9.000 -0.4344 0.08951 0.08264 -0.0354 1.0000 0.0425
-8.750 -0.4395 0.08484 0.07807 -0.0376 1.0000 0.0426
-8.500 -0.4464 0.08014 0.07350 -0.0398 1.0000 0.0425
-8.250 -0.4558 0.07539 0.06886 -0.0422 1.0000 0.0421
-8.000 -0.4660 0.06941 0.06297 -0.0463 1.0000 0.0416
-7.750 -0.4770 0.06351 0.05708 -0.0497 1.0000 0.0413
-7.500 -0.4864 0.05816 0.05165 -0.0518 1.0000 0.0409
-7.250 -0.4928 0.05300 0.04628 -0.0531 1.0000 0.0411
-7.000 -0.4945 0.04812 0.04107 -0.0537 1.0000 0.0420
-6.750 -0.4915 0.04350 0.03596 -0.0537 1.0000 0.0433
-6.500 -0.4835 0.03912 0.03093 -0.0532 1.0000 0.0448
-6.250 -0.4713 0.03616 0.02767 -0.0523 1.0000 0.0472
-6.000 -0.4567 0.03451 0.02587 -0.0512 1.0000 0.0525
-5.750 -0.4403 0.03186 0.02268 -0.0501 1.0000 0.0588
-5.500 -0.4236 0.03037 0.02105 -0.0490 1.0000 0.0673
-5.250 -0.4059 0.02888 0.01939 -0.0478 1.0000 0.0780
-5.000 -0.3876 0.02763 0.01791 -0.0468 1.0000 0.0930
-4.750 -0.3685 0.02654 0.01656 -0.0458 1.0000 0.1101
-4.500 -0.3493 0.02559 0.01552 -0.0447 1.0000 0.1261
-4.250 -0.3303 0.02489 0.01479 -0.0438 1.0000 0.1435
-4.000 -0.3039 0.02416 0.01391 -0.0441 0.9970 0.1641
-3.750 -0.2676 0.02343 0.01311 -0.0462 0.9892 0.1884
-3.500 -0.2307 0.02287 0.01243 -0.0484 0.9815 0.2188
-3.250 -0.1955 0.02233 0.01184 -0.0503 0.9729 0.2528
-3.000 -0.1603 0.02186 0.01140 -0.0522 0.9647 0.2946
-2.750 -0.1245 0.02140 0.01108 -0.0541 0.9566 0.3449
-2.500 -0.0922 0.02099 0.01080 -0.0553 0.9475 0.4039
-2.250 -0.0575 0.02059 0.01063 -0.0567 0.9399 0.4788
-2.000 -0.0283 0.02021 0.01055 -0.0568 0.9306 0.5629
-1.750 -0.0008 0.01986 0.01052 -0.0561 0.9219 0.6626
-1.500 0.0296 0.01954 0.01050 -0.0553 0.9145 0.7872
-1.250 0.0932 0.01922 0.01018 -0.0615 0.9093 0.9938
-1.000 0.1313 0.01935 0.00997 -0.0640 0.9007 1.0000
-0.750 0.1631 0.01950 0.00987 -0.0652 0.8905 1.0000
-0.500 0.1986 0.01963 0.00979 -0.0669 0.8821 1.0000
-0.250 0.2309 0.01979 0.00975 -0.0680 0.8724 1.0000
0.000 0.2602 0.01999 0.00979 -0.0685 0.8620 1.0000
0.250 0.2928 0.02015 0.00982 -0.0694 0.8530 1.0000
0.500 0.3244 0.02031 0.00987 -0.0701 0.8434 1.0000
0.750 0.3519 0.02054 0.01001 -0.0702 0.8324 1.0000
1.000 0.3815 0.02073 0.01013 -0.0705 0.8222 1.0000
1.250 0.4151 0.02083 0.01017 -0.0713 0.8135 1.0000
1.500 0.4412 0.02107 0.01038 -0.0709 0.8016 1.0000
1.750 0.4680 0.02129 0.01058 -0.0706 0.7899 1.0000
2.000 0.4957 0.02149 0.01076 -0.0704 0.7784 1.0000
2.250 0.5245 0.02163 0.01090 -0.0702 0.7672 1.0000
2.500 0.5547 0.02171 0.01101 -0.0701 0.7564 1.0000
2.750 0.5807 0.02191 0.01123 -0.0695 0.7434 1.0000
3.000 0.6066 0.02209 0.01145 -0.0688 0.7300 1.0000
3.250 0.6327 0.02225 0.01169 -0.0680 0.7164 1.0000
3.500 0.6590 0.02238 0.01188 -0.0672 0.7022 1.0000
3.750 0.6852 0.02249 0.01205 -0.0664 0.6875 1.0000
4.000 0.7117 0.02257 0.01220 -0.0655 0.6722 1.0000
4.250 0.7360 0.02272 0.01247 -0.0644 0.6551 1.0000
4.500 0.7598 0.02288 0.01272 -0.0631 0.6367 1.0000
4.750 0.7849 0.02294 0.01287 -0.0619 0.6180 1.0000
5.000 0.8091 0.02304 0.01306 -0.0607 0.5978 1.0000
5.250 0.8325 0.02316 0.01332 -0.0592 0.5753 1.0000
5.500 0.8549 0.02333 0.01358 -0.0577 0.5507 1.0000
5.750 0.8771 0.02350 0.01382 -0.0562 0.5240 1.0000
6.000 0.8985 0.02373 0.01410 -0.0545 0.4944 1.0000
6.250 0.9192 0.02401 0.01444 -0.0528 0.4621 1.0000
6.500 0.9384 0.02444 0.01484 -0.0510 0.4268 1.0000
6.750 0.9564 0.02500 0.01531 -0.0491 0.3903 1.0000
7.000 0.9727 0.02576 0.01598 -0.0472 0.3530 1.0000
7.250 0.9879 0.02669 0.01677 -0.0452 0.3183 1.0000
7.500 1.0020 0.02776 0.01777 -0.0434 0.2846 1.0000
7.750 1.0153 0.02894 0.01892 -0.0416 0.2546 1.0000
8.000 1.0280 0.03021 0.02014 -0.0397 0.2276 1.0000
8.250 1.0400 0.03157 0.02143 -0.0379 0.2039 1.0000
8.500 1.0523 0.03299 0.02285 -0.0362 0.1828 1.0000
8.750 1.0644 0.03449 0.02430 -0.0346 0.1657 1.0000
9.000 1.0766 0.03603 0.02589 -0.0329 0.1490 1.0000
9.250 1.0891 0.03761 0.02752 -0.0313 0.1354 1.0000
9.500 1.1022 0.03927 0.02919 -0.0298 0.1241 1.0000
9.750 1.1130 0.04095 0.03107 -0.0282 0.1129 1.0000
10.000 1.1256 0.04282 0.03315 -0.0267 0.1031 1.0000
10.250 1.1392 0.04483 0.03525 -0.0255 0.0952 1.0000
10.500 1.1469 0.04677 0.03733 -0.0239 0.0876 1.0000
10.750 1.1560 0.04915 0.03995 -0.0225 0.0809 1.0000
11.000 1.1641 0.05150 0.04249 -0.0212 0.0755 1.0000
11.250 1.1682 0.05414 0.04528 -0.0199 0.0704 1.0000
11.500 1.1661 0.05710 0.04859 -0.0186 0.0659 1.0000
11.750 1.1681 0.05987 0.05147 -0.0176 0.0624 1.0000
12.000 1.1682 0.06329 0.05505 -0.0168 0.0596 1.0000
12.250 1.1553 0.06769 0.05987 -0.0166 0.0577 1.0000
12.500 1.1408 0.07242 0.06493 -0.0170 0.0560 1.0000
12.750 1.1247 0.07759 0.07037 -0.0182 0.0548 1.0000
13.000 1.1061 0.08352 0.07654 -0.0204 0.0542 1.0000
13.250 1.0829 0.09073 0.08399 -0.0237 0.0542 1.0000
13.500 1.0532 0.10000 0.09348 -0.0289 0.0557 1.0000
13.750 1.0232 0.11048 0.10410 -0.0353 0.0574 1.0000
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Polar data table (+)
Polar graphs
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