MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 94 16.03% (mh94-il) Reynolds number: 50,000 Max Cl/Cd: 29.5 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh94-il-50000.txt Download as CSV file: xf-mh94-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 94 16.03%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4918 0.11562 0.10799 -0.0431 1.0000 0.1378
-11.750 -0.4850 0.11140 0.10376 -0.0428 1.0000 0.1339
-11.500 -0.6360 0.08448 0.07683 -0.0613 1.0000 0.1102
-11.250 -0.6589 0.07943 0.07177 -0.0615 1.0000 0.1093
-11.000 -0.6844 0.07496 0.06726 -0.0609 1.0000 0.1080
-10.750 -0.7155 0.07111 0.06334 -0.0590 1.0000 0.1067
-10.500 -0.7508 0.06803 0.06016 -0.0552 1.0000 0.1054
-10.250 -0.7811 0.06528 0.05728 -0.0507 1.0000 0.1045
-10.000 -0.8052 0.06218 0.05398 -0.0465 1.0000 0.1037
-9.750 -0.8223 0.05924 0.05081 -0.0426 1.0000 0.1034
-9.500 -0.8326 0.05644 0.04776 -0.0390 1.0000 0.1038
-9.250 -0.8380 0.05373 0.04479 -0.0356 1.0000 0.1046
-9.000 -0.8395 0.05107 0.04185 -0.0325 1.0000 0.1058
-8.750 -0.8373 0.04848 0.03892 -0.0295 1.0000 0.1072
-8.500 -0.8313 0.04595 0.03602 -0.0267 1.0000 0.1088
-8.250 -0.8222 0.04358 0.03327 -0.0241 1.0000 0.1110
-8.000 -0.8020 0.04148 0.03133 -0.0230 1.0000 0.1168
-7.750 -0.7883 0.03965 0.02919 -0.0207 1.0000 0.1227
-7.500 -0.7663 0.03776 0.02748 -0.0194 1.0000 0.1316
-7.250 -0.7470 0.03607 0.02588 -0.0177 1.0000 0.1435
-7.000 -0.7305 0.03449 0.02443 -0.0156 1.0000 0.1604
-6.750 -0.7182 0.03280 0.02298 -0.0130 1.0000 0.1854
-6.500 -0.7132 0.03087 0.02153 -0.0096 1.0000 0.2266
-6.250 -0.7183 0.02854 0.02022 -0.0049 1.0000 0.3117
-6.000 -0.7215 0.02803 0.02062 0.0013 1.0000 0.4288
-5.750 -0.7117 0.02925 0.02203 0.0067 1.0000 0.4913
-5.500 -0.6989 0.03056 0.02335 0.0116 1.0000 0.5337
-5.250 -0.6803 0.03282 0.02568 0.0172 1.0000 0.5657
-5.000 -0.6632 0.03475 0.02760 0.0227 1.0000 0.5954
-4.750 -0.6415 0.03704 0.02985 0.0283 1.0000 0.6215
-4.500 -0.6316 0.03743 0.03013 0.0325 1.0000 0.6477
-4.250 -0.6127 0.03845 0.03107 0.0367 1.0000 0.6686
-4.000 -0.5964 0.03884 0.03135 0.0401 1.0000 0.6882
-3.750 -0.5829 0.03881 0.03122 0.0432 1.0000 0.7071
-3.500 -0.5714 0.03856 0.03087 0.0461 1.0000 0.7257
-3.250 -0.5490 0.03887 0.03107 0.0483 1.0000 0.7418
-3.000 -0.5304 0.03881 0.03091 0.0503 1.0000 0.7585
-2.750 -0.5139 0.03858 0.03058 0.0522 1.0000 0.7755
-2.500 -0.4991 0.03823 0.03015 0.0540 1.0000 0.7924
-2.250 -0.4839 0.03788 0.02971 0.0556 1.0000 0.8097
-2.000 -0.4686 0.03753 0.02927 0.0569 1.0000 0.8268
-1.750 -0.4520 0.03721 0.02888 0.0578 1.0000 0.8439
-1.500 -0.4339 0.03695 0.02853 0.0584 1.0000 0.8607
-1.250 -0.4045 0.03697 0.02846 0.0570 1.0000 0.8769
-1.000 -0.3631 0.03722 0.02861 0.0534 1.0000 0.8917
-0.750 -0.3201 0.03750 0.02879 0.0490 1.0000 0.9064
-0.500 -0.2742 0.03784 0.02904 0.0437 1.0000 0.9207
-0.250 -0.2307 0.03819 0.02933 0.0385 1.0000 0.9352
0.000 -0.1864 0.03863 0.02971 0.0328 1.0000 0.9498
0.250 -0.0955 0.03991 0.03090 0.0185 0.9842 0.9616
0.500 -0.0025 0.04078 0.03171 0.0040 0.9629 0.9728
0.750 0.0967 0.04134 0.03225 -0.0113 0.9425 0.9843
1.000 0.1783 0.04126 0.03218 -0.0232 0.9198 0.9950
1.250 0.2481 0.04097 0.03192 -0.0325 0.8985 1.0000
1.500 0.3018 0.04050 0.03146 -0.0383 0.8780 1.0000
1.750 0.3275 0.04014 0.03114 -0.0393 0.8542 1.0000
2.000 0.3688 0.03952 0.03056 -0.0423 0.8322 1.0000
2.250 0.4194 0.03857 0.02966 -0.0461 0.8112 1.0000
2.500 0.4808 0.03710 0.02828 -0.0509 0.7912 1.0000
2.750 0.5627 0.03476 0.02604 -0.0579 0.7713 1.0000
3.000 0.5919 0.03379 0.02512 -0.0573 0.7452 1.0000
3.250 0.6607 0.03135 0.02273 -0.0614 0.7192 1.0000
3.500 0.7016 0.02991 0.02127 -0.0618 0.6886 1.0000
3.750 0.7425 0.02859 0.01986 -0.0620 0.6551 1.0000
4.000 0.7717 0.02785 0.01895 -0.0608 0.6201 1.0000
4.250 0.7911 0.02757 0.01850 -0.0585 0.5855 1.0000
4.500 0.8014 0.02768 0.01847 -0.0550 0.5521 1.0000
4.750 0.8132 0.02785 0.01848 -0.0519 0.5202 1.0000
5.000 0.8282 0.02807 0.01842 -0.0492 0.4893 1.0000
5.250 0.8331 0.02856 0.01881 -0.0453 0.4611 1.0000
5.500 0.8463 0.02902 0.01901 -0.0426 0.4340 1.0000
5.750 0.8493 0.02969 0.01962 -0.0385 0.4103 1.0000
6.000 0.8555 0.03038 0.02018 -0.0350 0.3884 1.0000
6.250 0.8629 0.03114 0.02082 -0.0316 0.3686 1.0000
6.500 0.8698 0.03199 0.02158 -0.0282 0.3510 1.0000
6.750 0.8776 0.03293 0.02245 -0.0251 0.3352 1.0000
7.000 0.8899 0.03398 0.02340 -0.0226 0.3208 1.0000
7.250 0.9105 0.03511 0.02432 -0.0215 0.3071 1.0000
7.500 0.9129 0.03644 0.02587 -0.0179 0.2962 1.0000
7.750 0.9304 0.03789 0.02728 -0.0166 0.2859 1.0000
8.000 0.9427 0.03947 0.02896 -0.0146 0.2769 1.0000
8.250 0.9596 0.04122 0.03072 -0.0134 0.2690 1.0000
8.500 0.9636 0.04314 0.03290 -0.0106 0.2621 1.0000
8.750 0.9952 0.04475 0.03430 -0.0114 0.2545 1.0000
9.000 0.9851 0.04736 0.03733 -0.0072 0.2511 1.0000
9.250 0.9755 0.05017 0.04046 -0.0034 0.2477 1.0000
9.500 0.9688 0.05298 0.04348 -0.0003 0.2442 1.0000
9.750 1.0040 0.05453 0.04491 -0.0014 0.2382 1.0000
10.000 0.9905 0.05794 0.04853 0.0020 0.2361 1.0000
10.250 0.9568 0.06197 0.05282 0.0067 0.2357 1.0000
10.500 0.9131 0.06692 0.05796 0.0110 0.2360 1.0000
10.750 0.8660 0.07353 0.06468 0.0128 0.2369 1.0000
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Polar data table (+)
Polar graphs
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