MH 23 8% (mh23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.86 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh23-il-1000000.txt Download as CSV file: xf-mh23-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4589 0.04719 0.04572 -0.0462 0.9941 0.0045
-7.500 -0.4713 0.03791 0.03625 -0.0501 0.9900 0.0048
-7.250 -0.4673 0.03212 0.03028 -0.0520 0.9873 0.0051
-7.000 -0.4534 0.02824 0.02625 -0.0535 0.9855 0.0054
-6.750 -0.4375 0.02465 0.02246 -0.0545 0.9838 0.0058
-6.500 -0.4202 0.02106 0.01867 -0.0550 0.9818 0.0065
-6.250 -0.4066 0.01829 0.01571 -0.0536 0.9781 0.0074
-6.000 -0.3744 0.01882 0.01620 -0.0535 0.9766 0.0093
-5.750 -0.3576 0.01640 0.01355 -0.0524 0.9734 0.0094
-5.500 -0.3414 0.01393 0.01081 -0.0511 0.9701 0.0095
-3.500 -0.1962 0.01089 0.00574 -0.0388 0.9471 0.0085
-3.250 -0.1762 0.00968 0.00440 -0.0367 0.9437 0.0074
-3.000 -0.1546 0.00897 0.00355 -0.0350 0.9399 0.0067
-2.750 -0.1313 0.00851 0.00298 -0.0337 0.9359 0.0064
-2.500 -0.1068 0.00820 0.00257 -0.0327 0.9324 0.0062
-2.250 -0.0820 0.00799 0.00228 -0.0318 0.9292 0.0063
-2.000 -0.0564 0.00781 0.00203 -0.0312 0.9247 0.0072
-1.750 -0.0350 0.00710 0.00174 -0.0299 0.9203 0.1322
-1.500 -0.0168 0.00615 0.00156 -0.0282 0.9163 0.3608
-1.250 -0.0008 0.00522 0.00145 -0.0261 0.9107 0.5982
-1.000 0.0097 0.00420 0.00149 -0.0218 0.9054 0.8925
-0.750 0.0416 0.00423 0.00156 -0.0223 0.9016 0.9302
-0.500 0.0705 0.00427 0.00159 -0.0223 0.8958 0.9444
-0.250 0.0960 0.00431 0.00157 -0.0215 0.8906 0.9553
0.000 0.1319 0.00438 0.00162 -0.0231 0.8841 0.9597
0.250 0.1636 0.00446 0.00167 -0.0237 0.8771 0.9674
0.500 0.2062 0.00453 0.00173 -0.0269 0.8681 0.9704
0.750 0.2466 0.00457 0.00174 -0.0296 0.8562 0.9724
1.000 0.2817 0.00459 0.00171 -0.0311 0.8380 0.9747
1.250 0.3135 0.00467 0.00168 -0.0319 0.8071 0.9779
1.500 0.3400 0.00487 0.00169 -0.0315 0.7615 0.9818
1.750 0.3753 0.00509 0.00170 -0.0332 0.7073 0.9833
2.000 0.4108 0.00536 0.00175 -0.0351 0.6516 0.9854
2.250 0.4456 0.00566 0.00182 -0.0369 0.5909 0.9881
2.500 0.4779 0.00598 0.00190 -0.0381 0.5280 0.9910
2.750 0.5076 0.00634 0.00202 -0.0388 0.4653 0.9938
3.000 0.5415 0.00663 0.00210 -0.0405 0.4027 0.9953
3.250 0.5738 0.00695 0.00218 -0.0420 0.3423 0.9969
3.500 0.6055 0.00722 0.00228 -0.0432 0.2944 0.9986
3.750 0.6360 0.00759 0.00241 -0.0442 0.2364 0.9999
4.000 0.6583 0.00797 0.00260 -0.0434 0.1866 1.0000
4.250 0.6779 0.00855 0.00283 -0.0421 0.1168 1.0000
4.500 0.6996 0.00886 0.00303 -0.0411 0.0902 1.0000
4.750 0.7210 0.00922 0.00326 -0.0401 0.0616 1.0000
5.000 0.7426 0.00954 0.00349 -0.0390 0.0433 1.0000
5.250 0.7640 0.00988 0.00375 -0.0379 0.0278 1.0000
5.500 0.7850 0.01026 0.00406 -0.0368 0.0148 1.0000
5.750 0.8055 0.01069 0.00445 -0.0355 0.0056 1.0000
6.000 0.8261 0.01113 0.00493 -0.0341 0.0029 1.0000
6.250 0.8465 0.01159 0.00552 -0.0326 0.0025 1.0000
6.500 0.8665 0.01207 0.00611 -0.0311 0.0023 1.0000
6.750 0.8851 0.01272 0.00688 -0.0293 0.0022 1.0000
7.000 0.9027 0.01345 0.00774 -0.0273 0.0022 1.0000
7.250 0.9187 0.01434 0.00879 -0.0249 0.0022 1.0000
7.500 0.9327 0.01545 0.01007 -0.0223 0.0023 1.0000
7.750 0.9430 0.01715 0.01202 -0.0188 0.0024 1.0000
8.000 0.9512 0.01947 0.01464 -0.0150 0.0026 1.0000
8.250 0.9573 0.02241 0.01794 -0.0109 0.0028 1.0000
8.500 0.9581 0.02596 0.02190 -0.0062 0.0032 1.0000
8.750 0.9468 0.03066 0.02708 -0.0001 0.0035 1.0000
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Polar data table (+)
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