MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 200,000 Max Cl/Cd: 55.56 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh91-il-200000-n5.txt Download as CSV file: xf-mh91-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7077 0.10982 0.10604 0.0088 1.0000 0.0124
-13.750 -0.7606 0.09157 0.08754 -0.0033 1.0000 0.0121
-13.500 -0.7908 0.08098 0.07675 -0.0108 1.0000 0.0119
-13.250 -0.8145 0.07289 0.06845 -0.0163 1.0000 0.0117
-13.000 -0.8394 0.06558 0.06089 -0.0207 1.0000 0.0118
-12.750 -0.8557 0.06027 0.05538 -0.0232 1.0000 0.0116
-12.500 -0.8742 0.05519 0.05005 -0.0248 1.0000 0.0117
-12.250 -0.8880 0.05110 0.04570 -0.0253 1.0000 0.0118
-12.000 -0.8988 0.04756 0.04192 -0.0249 1.0000 0.0118
-11.750 -0.9038 0.04474 0.03888 -0.0240 1.0000 0.0118
-11.500 -0.9085 0.04198 0.03586 -0.0226 1.0000 0.0120
-11.250 -0.9078 0.03970 0.03337 -0.0211 1.0000 0.0120
-11.000 -0.9052 0.03754 0.03099 -0.0193 1.0000 0.0121
-10.750 -0.8996 0.03557 0.02878 -0.0175 1.0000 0.0123
-10.500 -0.8905 0.03384 0.02687 -0.0159 1.0000 0.0124
-10.250 -0.8797 0.03220 0.02503 -0.0142 1.0000 0.0126
-10.000 -0.8667 0.03076 0.02345 -0.0127 1.0000 0.0127
-9.750 -0.8530 0.02947 0.02212 -0.0113 1.0000 0.0130
-9.500 -0.8380 0.02832 0.02091 -0.0099 1.0000 0.0131
-9.250 -0.8225 0.02736 0.01992 -0.0085 1.0000 0.0135
-9.000 -0.8049 0.02648 0.01898 -0.0074 1.0000 0.0141
-8.750 -0.7862 0.02550 0.01790 -0.0064 1.0000 0.0148
-8.500 -0.7666 0.02454 0.01683 -0.0054 1.0000 0.0154
-8.250 -0.7395 0.02347 0.01573 -0.0061 0.9469 0.0159
-8.000 -0.7167 0.02261 0.01482 -0.0057 0.9142 0.0165
-7.750 -0.6992 0.02189 0.01400 -0.0040 0.8889 0.0170
-7.500 -0.6827 0.02119 0.01319 -0.0020 0.8678 0.0177
-7.250 -0.6657 0.02054 0.01241 0.0000 0.8495 0.0183
-7.000 -0.6486 0.01987 0.01165 0.0019 0.8327 0.0190
-6.750 -0.6299 0.01927 0.01098 0.0035 0.8172 0.0200
-6.500 -0.6103 0.01872 0.01031 0.0050 0.8025 0.0214
-6.250 -0.5901 0.01817 0.00968 0.0064 0.7885 0.0231
-6.000 -0.5689 0.01769 0.00911 0.0076 0.7749 0.0261
-5.750 -0.5471 0.01719 0.00854 0.0088 0.7610 0.0301
-5.500 -0.5252 0.01667 0.00799 0.0099 0.7479 0.0355
-5.250 -0.5035 0.01613 0.00745 0.0110 0.7353 0.0462
-5.000 -0.4822 0.01553 0.00692 0.0121 0.7224 0.0681
-4.750 -0.4616 0.01481 0.00642 0.0133 0.7096 0.1125
-4.500 -0.4421 0.01403 0.00595 0.0145 0.6974 0.1828
-4.250 -0.4232 0.01327 0.00555 0.0158 0.6853 0.2671
-4.000 -0.4025 0.01269 0.00526 0.0170 0.6727 0.3397
-3.750 -0.3812 0.01222 0.00501 0.0182 0.6608 0.4024
-3.500 -0.3594 0.01184 0.00480 0.0194 0.6488 0.4601
-3.250 -0.3366 0.01151 0.00464 0.0205 0.6362 0.5144
-3.000 -0.3133 0.01124 0.00452 0.0217 0.6244 0.5647
-2.750 -0.2887 0.01107 0.00441 0.0226 0.6125 0.6032
-2.500 -0.2628 0.01095 0.00433 0.0233 0.6000 0.6332
-2.250 -0.2365 0.01088 0.00427 0.0240 0.5881 0.6610
-2.000 -0.2101 0.01085 0.00422 0.0246 0.5763 0.6865
-1.750 -0.1832 0.01084 0.00420 0.0252 0.5638 0.7102
-1.500 -0.1562 0.01086 0.00418 0.0257 0.5519 0.7305
-1.250 -0.1291 0.01091 0.00416 0.0262 0.5402 0.7479
-1.000 -0.1017 0.01096 0.00416 0.0266 0.5278 0.7632
-0.750 -0.0742 0.01102 0.00416 0.0270 0.5161 0.7768
-0.500 -0.0470 0.01110 0.00416 0.0274 0.5047 0.7898
-0.250 -0.0199 0.01117 0.00416 0.0278 0.4926 0.8022
0.000 0.0080 0.01127 0.00421 0.0281 0.4811 0.8124
0.250 0.0349 0.01137 0.00422 0.0285 0.4701 0.8232
0.500 0.0626 0.01148 0.00427 0.0288 0.4584 0.8329
0.750 0.0898 0.01159 0.00432 0.0292 0.4475 0.8423
1.000 0.1167 0.01173 0.00437 0.0296 0.4369 0.8519
1.250 0.1442 0.01184 0.00446 0.0299 0.4259 0.8607
1.500 0.1711 0.01199 0.00454 0.0303 0.4159 0.8699
1.750 0.1983 0.01212 0.00462 0.0307 0.4055 0.8778
2.000 0.2262 0.01227 0.00472 0.0308 0.3958 0.8847
2.250 0.2518 0.01240 0.00477 0.0313 0.3864 0.8928
2.500 0.2814 0.01255 0.00489 0.0312 0.3769 0.8979
3.000 0.3355 0.01283 0.00509 0.0316 0.3593 0.9111
3.250 0.3654 0.01302 0.00521 0.0312 0.3509 0.9159
3.500 0.3934 0.01316 0.00535 0.0312 0.3427 0.9221
3.750 0.4207 0.01334 0.00546 0.0312 0.3350 0.9280
4.000 0.4527 0.01351 0.00563 0.0304 0.3267 0.9322
4.250 0.4815 0.01370 0.00578 0.0301 0.3194 0.9380
4.500 0.5103 0.01387 0.00595 0.0298 0.3127 0.9437
4.750 0.5439 0.01409 0.00614 0.0286 0.3051 0.9473
5.000 0.5752 0.01430 0.00634 0.0277 0.2983 0.9521
5.250 0.6037 0.01449 0.00654 0.0274 0.2914 0.9577
5.750 0.6718 0.01496 0.00700 0.0244 0.2782 0.9638
6.000 0.7025 0.01520 0.00723 0.0235 0.2717 0.9681
6.250 0.7337 0.01545 0.00749 0.0225 0.2659 0.9718
6.500 0.7681 0.01569 0.00777 0.0208 0.2594 0.9745
6.750 0.7999 0.01599 0.00804 0.0195 0.2535 0.9779
7.000 0.8301 0.01624 0.00835 0.0187 0.2476 0.9821
7.250 0.8631 0.01653 0.00865 0.0172 0.2415 0.9850
7.500 0.8952 0.01686 0.00898 0.0158 0.2360 0.9883
7.750 0.9264 0.01714 0.00934 0.0147 0.2299 0.9920
8.000 0.9576 0.01749 0.00970 0.0133 0.2240 0.9956
8.250 0.9894 0.01784 0.01010 0.0119 0.2182 0.9992
8.500 1.0084 0.01815 0.01046 0.0130 0.2128 1.0000
8.750 1.0219 0.01850 0.01081 0.0151 0.2084 1.0000
9.000 1.0359 0.01885 0.01119 0.0172 0.2042 1.0000
9.250 1.0499 0.01918 0.01160 0.0192 0.1997 1.0000
9.500 1.0629 0.01956 0.01199 0.0213 0.1954 1.0000
9.750 1.0756 0.02001 0.01243 0.0234 0.1915 1.0000
10.000 1.0906 0.02039 0.01291 0.0252 0.1870 1.0000
10.250 1.1047 0.02084 0.01341 0.0269 0.1826 1.0000
10.500 1.1174 0.02138 0.01393 0.0287 0.1785 1.0000
10.750 1.1322 0.02189 0.01453 0.0302 0.1744 1.0000
11.000 1.1455 0.02243 0.01515 0.0318 0.1699 1.0000
11.250 1.1542 0.02306 0.01580 0.0340 0.1661 1.0000
11.500 1.1628 0.02379 0.01656 0.0359 0.1624 1.0000
11.750 1.1735 0.02453 0.01741 0.0374 0.1581 1.0000
12.000 1.1820 0.02544 0.01837 0.0388 0.1540 1.0000
12.250 1.1886 0.02655 0.01949 0.0400 0.1505 1.0000
12.500 1.1990 0.02757 0.02063 0.0408 0.1464 1.0000
12.750 1.2068 0.02880 0.02194 0.0416 0.1422 1.0000
13.000 1.2116 0.03029 0.02346 0.0422 0.1385 1.0000
13.250 1.2183 0.03178 0.02504 0.0427 0.1349 1.0000
13.500 1.2242 0.03340 0.02677 0.0430 0.1308 1.0000
13.750 1.2274 0.03530 0.02872 0.0431 0.1273 1.0000
14.000 1.2288 0.03744 0.03089 0.0431 0.1240 1.0000
14.250 1.2325 0.03949 0.03308 0.0429 0.1203 1.0000
14.500 1.2332 0.04189 0.03557 0.0425 0.1169 1.0000
14.750 1.2311 0.04462 0.03833 0.0420 0.1140 1.0000
15.000 1.2300 0.04734 0.04115 0.0414 0.1110 1.0000
15.250 1.2284 0.05024 0.04417 0.0405 0.1078 1.0000
15.500 1.2241 0.05351 0.04750 0.0395 0.1049 1.0000
15.750 1.2187 0.05700 0.05103 0.0383 0.1024 1.0000
16.000 1.2145 0.06050 0.05464 0.0370 0.0998 1.0000
16.250 1.2090 0.06431 0.05857 0.0354 0.0968 1.0000
16.500 1.2025 0.06833 0.06267 0.0337 0.0943 1.0000
16.750 1.1949 0.07256 0.06693 0.0318 0.0920 1.0000
17.000 1.1885 0.07674 0.07119 0.0299 0.0897 1.0000
17.250 1.1802 0.08137 0.07597 0.0278 0.0872 1.0000
17.500 1.1721 0.08605 0.08074 0.0255 0.0849 1.0000
17.750 1.1642 0.09069 0.08543 0.0232 0.0828 1.0000
18.000 1.1590 0.09494 0.08969 0.0212 0.0807 1.0000
18.250 1.1489 0.10022 0.09513 0.0185 0.0787 1.0000
18.500 1.1387 0.10558 0.10060 0.0157 0.0766 1.0000
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Polar data table (+)
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