MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 200,000 Max Cl/Cd: 52.66 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh91-il-200000.txt Download as CSV file: xf-mh91-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5964 0.08950 0.08630 -0.0090 1.0000 0.0689
-10.500 -0.6406 0.07788 0.07460 -0.0189 1.0000 0.0688
-10.250 -0.6799 0.07118 0.06777 -0.0230 1.0000 0.0692
-10.000 -0.7141 0.06688 0.06331 -0.0232 1.0000 0.0699
-9.750 -0.8569 0.04493 0.03914 -0.0116 1.0000 0.0299
-9.500 -0.8419 0.04182 0.03598 -0.0109 1.0000 0.0293
-9.250 -0.8328 0.03866 0.03254 -0.0091 1.0000 0.0285
-9.000 -0.8216 0.03553 0.02905 -0.0073 1.0000 0.0278
-8.750 -0.8068 0.03265 0.02576 -0.0057 1.0000 0.0272
-8.500 -0.7871 0.03043 0.02327 -0.0047 1.0000 0.0271
-8.250 -0.7645 0.02859 0.02124 -0.0041 1.0000 0.0272
-8.000 -0.7408 0.02712 0.01969 -0.0037 1.0000 0.0279
-7.750 -0.7181 0.02595 0.01839 -0.0032 1.0000 0.0291
-7.500 -0.6997 0.02493 0.01722 -0.0020 1.0000 0.0299
-7.250 -0.6586 0.02314 0.01546 -0.0050 0.9828 0.0312
-7.000 -0.6172 0.02172 0.01405 -0.0078 0.9645 0.0327
-6.750 -0.5821 0.02058 0.01285 -0.0092 0.9443 0.0343
-6.500 -0.5612 0.01958 0.01184 -0.0078 0.9208 0.0361
-6.250 -0.5463 0.01892 0.01117 -0.0052 0.8995 0.0384
-6.000 -0.5325 0.01825 0.01042 -0.0023 0.8808 0.0417
-5.750 -0.5165 0.01770 0.00982 0.0001 0.8636 0.0472
-5.500 -0.5016 0.01692 0.00904 0.0026 0.8474 0.0552
-5.250 -0.4873 0.01590 0.00814 0.0051 0.8320 0.0776
-5.000 -0.4811 0.01406 0.00718 0.0084 0.8175 0.2167
-4.750 -0.4684 0.01310 0.00676 0.0109 0.8039 0.3376
-4.500 -0.4515 0.01256 0.00648 0.0131 0.7911 0.4124
-4.250 -0.4322 0.01214 0.00627 0.0150 0.7772 0.4774
-4.000 -0.4114 0.01182 0.00612 0.0167 0.7636 0.5334
-3.750 -0.3896 0.01158 0.00601 0.0183 0.7511 0.5829
-3.500 -0.3671 0.01142 0.00591 0.0200 0.7390 0.6275
-3.250 -0.3430 0.01132 0.00591 0.0213 0.7252 0.6674
-3.000 -0.3185 0.01133 0.00597 0.0228 0.7122 0.7038
-2.750 -0.2938 0.01140 0.00597 0.0241 0.7003 0.7334
-2.500 -0.2672 0.01148 0.00603 0.0251 0.6870 0.7547
-2.250 -0.2406 0.01160 0.00609 0.0261 0.6738 0.7738
-2.000 -0.2141 0.01174 0.00615 0.0271 0.6614 0.7912
-1.750 -0.1878 0.01189 0.00619 0.0282 0.6491 0.8073
-1.500 -0.1616 0.01203 0.00626 0.0291 0.6354 0.8223
-1.250 -0.1336 0.01222 0.00638 0.0299 0.6225 0.8341
-1.000 -0.1058 0.01241 0.00644 0.0306 0.6103 0.8448
-0.750 -0.0802 0.01253 0.00647 0.0315 0.5972 0.8574
-0.500 -0.0490 0.01275 0.00662 0.0316 0.5836 0.8651
-0.250 -0.0230 0.01287 0.00663 0.0325 0.5711 0.8761
0.000 0.0099 0.01311 0.00673 0.0322 0.5585 0.8829
0.250 0.0359 0.01320 0.00676 0.0329 0.5451 0.8934
0.500 0.0726 0.01342 0.00689 0.0317 0.5312 0.8988
0.750 0.0975 0.01354 0.00690 0.0326 0.5194 0.9096
1.000 0.1389 0.01377 0.00699 0.0304 0.5061 0.9136
1.250 0.1779 0.01395 0.00710 0.0285 0.4918 0.9195
1.500 0.2096 0.01408 0.00716 0.0279 0.4792 0.9278
1.750 0.2561 0.01426 0.00723 0.0244 0.4656 0.9312
2.000 0.2956 0.01443 0.00724 0.0222 0.4535 0.9365
2.250 0.3273 0.01449 0.00730 0.0214 0.4413 0.9437
2.500 0.3699 0.01461 0.00734 0.0184 0.4290 0.9473
2.750 0.4058 0.01476 0.00735 0.0167 0.4185 0.9531
3.000 0.4395 0.01482 0.00742 0.0154 0.4074 0.9589
3.250 0.4798 0.01493 0.00746 0.0128 0.3966 0.9629
3.500 0.5128 0.01506 0.00751 0.0115 0.3870 0.9690
3.750 0.5507 0.01515 0.00760 0.0093 0.3768 0.9733
4.250 0.6223 0.01539 0.00777 0.0055 0.3585 0.9833
4.500 0.6616 0.01551 0.00779 0.0029 0.3498 0.9871
4.750 0.6985 0.01559 0.00791 0.0007 0.3408 0.9918
5.000 0.7356 0.01576 0.00800 -0.0016 0.3330 0.9958
5.250 0.7738 0.01582 0.00811 -0.0041 0.3241 1.0000
5.500 0.7951 0.01609 0.00827 -0.0033 0.3180 1.0000
5.750 0.8159 0.01626 0.00855 -0.0024 0.3113 1.0000
6.000 0.8367 0.01645 0.00873 -0.0015 0.3051 1.0000
6.250 0.8573 0.01675 0.00901 -0.0006 0.2993 1.0000
6.500 0.8774 0.01696 0.00930 0.0005 0.2929 1.0000
6.750 0.8973 0.01722 0.00952 0.0015 0.2874 1.0000
7.000 0.9167 0.01757 0.00990 0.0027 0.2819 1.0000
7.250 0.9355 0.01782 0.01022 0.0039 0.2758 1.0000
7.500 0.9544 0.01814 0.01048 0.0052 0.2707 1.0000
7.750 0.9722 0.01851 0.01092 0.0066 0.2652 1.0000
8.000 0.9894 0.01879 0.01127 0.0081 0.2595 1.0000
8.250 1.0072 0.01913 0.01155 0.0096 0.2546 1.0000
8.500 1.0232 0.01954 0.01203 0.0113 0.2494 1.0000
8.750 1.0387 0.01985 0.01243 0.0131 0.2441 1.0000
9.000 1.0551 0.02020 0.01274 0.0148 0.2395 1.0000
9.250 1.0705 0.02068 0.01327 0.0166 0.2348 1.0000
9.500 1.0844 0.02104 0.01373 0.0186 0.2296 1.0000
9.750 1.1003 0.02139 0.01408 0.0203 0.2250 1.0000
10.000 1.1168 0.02194 0.01461 0.0218 0.2204 1.0000
10.250 1.1303 0.02236 0.01518 0.0238 0.2153 1.0000
10.500 1.1466 0.02273 0.01557 0.0253 0.2104 1.0000
10.750 1.1646 0.02335 0.01614 0.0265 0.2058 1.0000
11.000 1.1776 0.02385 0.01682 0.0283 0.2006 1.0000
11.250 1.1937 0.02431 0.01729 0.0296 0.1957 1.0000
11.500 1.2107 0.02499 0.01795 0.0307 0.1909 1.0000
11.750 1.2212 0.02561 0.01875 0.0325 0.1859 1.0000
12.000 1.2347 0.02616 0.01931 0.0340 0.1811 1.0000
12.250 1.2482 0.02694 0.02008 0.0353 0.1764 1.0000
12.500 1.2503 0.02772 0.02103 0.0380 0.1720 1.0000
12.750 1.2579 0.02847 0.02182 0.0398 0.1677 1.0000
13.000 1.2705 0.02941 0.02269 0.0409 0.1631 1.0000
13.250 1.2696 0.03066 0.02415 0.0427 0.1591 1.0000
13.500 1.2748 0.03180 0.02535 0.0438 0.1547 1.0000
13.750 1.2900 0.03277 0.02619 0.0444 0.1503 1.0000
14.000 1.2848 0.03465 0.02833 0.0455 0.1468 1.0000
14.250 1.2861 0.03633 0.03012 0.0461 0.1429 1.0000
14.500 1.2937 0.03770 0.03146 0.0464 0.1391 1.0000
14.750 1.2961 0.03964 0.03347 0.0468 0.1355 1.0000
15.000 1.2913 0.04215 0.03615 0.0467 0.1321 1.0000
15.250 1.2929 0.04419 0.03825 0.0465 0.1286 1.0000
15.500 1.3057 0.04540 0.03934 0.0468 0.1247 1.0000
15.750 1.2933 0.04894 0.04314 0.0459 0.1223 1.0000
16.000 1.2857 0.05221 0.04656 0.0449 0.1192 1.0000
16.250 1.2858 0.05472 0.04910 0.0442 0.1161 1.0000
16.500 1.2979 0.05600 0.05028 0.0444 0.1127 1.0000
16.750 1.2799 0.06084 0.05537 0.0423 0.1106 1.0000
17.000 1.2679 0.06525 0.05996 0.0403 0.1082 1.0000
17.250 1.2638 0.06872 0.06350 0.0388 0.1054 1.0000
17.500 1.2773 0.06982 0.06449 0.0388 0.1023 1.0000
17.750 1.2619 0.07506 0.06992 0.0363 0.1003 1.0000
18.000 1.2388 0.08170 0.07678 0.0327 0.0984 1.0000
18.250 1.2204 0.08787 0.08312 0.0294 0.0963 1.0000
18.500 1.2221 0.09093 0.08619 0.0279 0.0937 1.0000
18.750 1.2386 0.09147 0.08663 0.0282 0.0905 1.0000
19.000 1.2001 0.10134 0.09679 0.0225 0.0894 1.0000
19.250 1.1329 0.11690 0.11267 0.0134 0.0886 1.0000
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Polar data table (+)
Polar graphs
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