MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 200,000 Max Cl/Cd: 52.52 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh93-il-200000.txt Download as CSV file: xf-mh93-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7668 0.05679 0.05257 -0.0253 1.0000 0.0333
-11.500 -0.7764 0.05257 0.04826 -0.0250 1.0000 0.0328
-11.250 -0.8652 0.05605 0.05122 -0.0207 1.0000 0.0329
-11.000 -0.9252 0.05015 0.04449 -0.0133 1.0000 0.0291
-10.750 -0.9164 0.04711 0.04136 -0.0121 1.0000 0.0287
-10.500 -0.9137 0.04423 0.03827 -0.0099 1.0000 0.0283
-10.250 -0.9090 0.04139 0.03517 -0.0078 1.0000 0.0279
-10.000 -0.9004 0.03865 0.03215 -0.0059 1.0000 0.0276
-9.750 -0.8876 0.03609 0.02930 -0.0043 1.0000 0.0273
-9.500 -0.8709 0.03383 0.02678 -0.0031 1.0000 0.0272
-9.250 -0.8513 0.03194 0.02468 -0.0022 1.0000 0.0276
-9.000 -0.8314 0.03045 0.02298 -0.0014 1.0000 0.0285
-8.750 -0.8098 0.02901 0.02129 -0.0007 1.0000 0.0292
-8.500 -0.7804 0.02715 0.01944 -0.0014 1.0000 0.0301
-8.250 -0.7519 0.02581 0.01812 -0.0020 1.0000 0.0308
-8.000 -0.7231 0.02456 0.01689 -0.0028 0.9959 0.0316
-7.750 -0.6801 0.02312 0.01537 -0.0058 0.9615 0.0333
-7.500 -0.6487 0.02186 0.01410 -0.0068 0.9342 0.0347
-7.250 -0.6333 0.02112 0.01335 -0.0045 0.9082 0.0366
-7.000 -0.6203 0.02054 0.01266 -0.0015 0.8863 0.0387
-6.750 -0.6098 0.01977 0.01189 0.0016 0.8674 0.0413
-6.500 -0.5964 0.01914 0.01120 0.0043 0.8508 0.0458
-6.250 -0.5829 0.01844 0.01047 0.0069 0.8355 0.0523
-6.000 -0.5697 0.01763 0.00967 0.0096 0.8214 0.0623
-5.750 -0.5590 0.01651 0.00875 0.0126 0.8083 0.0951
-5.500 -0.5541 0.01485 0.00787 0.0160 0.7946 0.2200
-5.250 -0.5431 0.01393 0.00743 0.0187 0.7820 0.3229
-5.000 -0.5283 0.01336 0.00710 0.0212 0.7708 0.3927
-4.750 -0.5108 0.01288 0.00686 0.0232 0.7577 0.4536
-4.500 -0.4916 0.01253 0.00668 0.0251 0.7460 0.5072
-4.250 -0.4713 0.01227 0.00650 0.0270 0.7352 0.5546
-4.000 -0.4489 0.01203 0.00642 0.0284 0.7226 0.5981
-3.750 -0.4259 0.01191 0.00636 0.0299 0.7116 0.6382
-3.500 -0.4020 0.01186 0.00637 0.0314 0.7001 0.6751
-3.250 -0.3766 0.01194 0.00649 0.0326 0.6883 0.7073
-3.000 -0.3511 0.01205 0.00653 0.0338 0.6779 0.7323
-2.750 -0.3238 0.01217 0.00664 0.0346 0.6655 0.7516
-2.500 -0.2969 0.01233 0.00672 0.0355 0.6545 0.7689
-2.250 -0.2705 0.01250 0.00677 0.0365 0.6436 0.7848
-2.000 -0.2430 0.01270 0.00692 0.0372 0.6316 0.7989
-1.750 -0.2133 0.01297 0.00709 0.0377 0.6210 0.8093
-1.500 -0.1865 0.01312 0.00716 0.0385 0.6092 0.8214
-1.250 -0.1564 0.01337 0.00733 0.0388 0.5979 0.8303
-1.000 -0.1290 0.01355 0.00738 0.0394 0.5874 0.8401
-0.750 -0.0978 0.01379 0.00757 0.0394 0.5751 0.8477
-0.500 -0.0712 0.01394 0.00760 0.0401 0.5648 0.8573
-0.250 -0.0373 0.01419 0.00776 0.0396 0.5530 0.8629
0.000 -0.0137 0.01428 0.00778 0.0407 0.5420 0.8737
0.250 0.0234 0.01456 0.00792 0.0396 0.5313 0.8777
0.500 0.0575 0.01475 0.00807 0.0388 0.5188 0.8839
0.750 0.0839 0.01486 0.00810 0.0393 0.5083 0.8926
1.000 0.1248 0.01512 0.00822 0.0373 0.4971 0.8963
1.250 0.1621 0.01531 0.00837 0.0357 0.4849 0.9021
1.500 0.1898 0.01542 0.00839 0.0359 0.4751 0.9102
1.750 0.2350 0.01558 0.00847 0.0327 0.4632 0.9130
2.000 0.2758 0.01572 0.00855 0.0302 0.4515 0.9171
2.250 0.2973 0.01582 0.00853 0.0314 0.4432 0.9261
2.500 0.3414 0.01590 0.00860 0.0282 0.4314 0.9286
2.750 0.3810 0.01603 0.00865 0.0258 0.4216 0.9322
3.000 0.4102 0.01611 0.00870 0.0254 0.4121 0.9389
3.250 0.4437 0.01622 0.00874 0.0242 0.4032 0.9435
3.500 0.4832 0.01629 0.00876 0.0217 0.3935 0.9470
3.750 0.5162 0.01642 0.00887 0.0205 0.3848 0.9522
4.000 0.5457 0.01651 0.00891 0.0199 0.3768 0.9577
4.250 0.5847 0.01663 0.00901 0.0174 0.3683 0.9610
4.500 0.6189 0.01672 0.00909 0.0159 0.3600 0.9657
4.750 0.6486 0.01690 0.00922 0.0152 0.3527 0.9709
5.000 0.6872 0.01696 0.00930 0.0127 0.3444 0.9742
5.250 0.7214 0.01717 0.00943 0.0111 0.3377 0.9786
5.500 0.7532 0.01727 0.00961 0.0099 0.3298 0.9832
5.750 0.7905 0.01741 0.00965 0.0076 0.3229 0.9864
6.000 0.8249 0.01756 0.00990 0.0058 0.3156 0.9905
6.250 0.8589 0.01770 0.01002 0.0041 0.3089 0.9942
6.500 0.8942 0.01790 0.01023 0.0021 0.3022 0.9975
6.750 0.9255 0.01807 0.01046 0.0008 0.2955 1.0000
7.000 0.9458 0.01834 0.01067 0.0017 0.2905 1.0000
7.250 0.9654 0.01865 0.01106 0.0027 0.2851 1.0000
7.500 0.9846 0.01890 0.01137 0.0038 0.2795 1.0000
7.750 1.0040 0.01917 0.01161 0.0048 0.2747 1.0000
8.000 1.0225 0.01957 0.01204 0.0060 0.2698 1.0000
8.250 1.0399 0.01985 0.01243 0.0073 0.2644 1.0000
8.500 1.0577 0.02014 0.01270 0.0087 0.2596 1.0000
8.750 1.0749 0.02059 0.01313 0.0101 0.2549 1.0000
9.000 1.0894 0.02092 0.01361 0.0118 0.2497 1.0000
9.250 1.1049 0.02122 0.01393 0.0135 0.2451 1.0000
9.500 1.1222 0.02172 0.01431 0.0149 0.2407 1.0000
9.750 1.1323 0.02210 0.01490 0.0174 0.2363 1.0000
10.000 1.1438 0.02246 0.01533 0.0197 0.2317 1.0000
10.250 1.1566 0.02281 0.01566 0.0218 0.2277 1.0000
10.500 1.1683 0.02334 0.01620 0.0240 0.2237 1.0000
10.750 1.1737 0.02376 0.01677 0.0272 0.2195 1.0000
11.000 1.1819 0.02413 0.01718 0.0300 0.2153 1.0000
11.250 1.1946 0.02456 0.01755 0.0321 0.2114 1.0000
11.500 1.2015 0.02516 0.01824 0.0348 0.2074 1.0000
11.750 1.2067 0.02567 0.01887 0.0377 0.2031 1.0000
12.000 1.2173 0.02613 0.01934 0.0397 0.1989 1.0000
12.250 1.2332 0.02680 0.01994 0.0409 0.1946 1.0000
12.500 1.2300 0.02754 0.02087 0.0445 0.1910 1.0000
12.750 1.2336 0.02828 0.02168 0.0468 0.1868 1.0000
13.000 1.2445 0.02895 0.02231 0.0481 0.1828 1.0000
13.250 1.2500 0.03006 0.02349 0.0496 0.1786 1.0000
13.500 1.2500 0.03133 0.02490 0.0511 0.1746 1.0000
13.750 1.2565 0.03238 0.02598 0.0521 0.1704 1.0000
14.000 1.2685 0.03343 0.02698 0.0527 0.1661 1.0000
14.250 1.2627 0.03539 0.02915 0.0536 0.1624 1.0000
14.500 1.2647 0.03700 0.03084 0.0541 0.1583 1.0000
14.750 1.2780 0.03799 0.03172 0.0545 0.1541 1.0000
15.000 1.2708 0.04052 0.03443 0.0547 0.1506 1.0000
15.250 1.2664 0.04296 0.03702 0.0545 0.1469 1.0000
15.500 1.2704 0.04473 0.03880 0.0544 0.1432 1.0000
15.750 1.2767 0.04647 0.04052 0.0545 0.1394 1.0000
16.000 1.2639 0.05005 0.04431 0.0536 0.1364 1.0000
16.250 1.2593 0.05293 0.04728 0.0528 0.1329 1.0000
16.500 1.2668 0.05456 0.04886 0.0525 0.1294 1.0000
16.750 1.2621 0.05773 0.05212 0.0516 0.1264 1.0000
17.000 1.2454 0.06244 0.05704 0.0496 0.1235 1.0000
17.250 1.2403 0.06591 0.06058 0.0482 0.1204 1.0000
17.500 1.2540 0.06692 0.06150 0.0481 0.1169 1.0000
17.750 1.2388 0.07190 0.06665 0.0459 0.1144 1.0000
18.000 1.2155 0.07828 0.07324 0.0427 0.1121 1.0000
18.250 1.2037 0.08316 0.07823 0.0402 0.1094 1.0000
18.500 1.2184 0.08410 0.07909 0.0400 0.1063 1.0000
18.750 1.2105 0.08847 0.08354 0.0380 0.1038 1.0000
19.000 1.1660 0.09892 0.09428 0.0322 0.1020 1.0000
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Polar data table (+)
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