MH 23 8% (mh23-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 200,000 Max Cl/Cd: 57.38 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh23-il-200000-n5.txt Download as CSV file: xf-mh23-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4109 0.09703 0.09366 -0.0274 1.0000 0.0204
-6.500 -0.5623 0.05457 0.05085 -0.0238 1.0000 0.0173
-6.250 -0.5575 0.05036 0.04646 -0.0230 0.9986 0.0157
-6.000 -0.5415 0.04447 0.04023 -0.0239 0.9950 0.0134
-5.750 -0.5245 0.03700 0.03210 -0.0226 0.9914 0.0107
-5.500 -0.5001 0.03465 0.02940 -0.0220 0.9884 0.0099
-5.000 -0.4542 0.02893 0.02296 -0.0216 0.9831 0.0091
-4.750 -0.4307 0.02588 0.01944 -0.0211 0.9806 0.0089
-4.500 -0.4086 0.02347 0.01661 -0.0199 0.9772 0.0087
-4.250 -0.3824 0.02140 0.01417 -0.0194 0.9745 0.0086
-4.000 -0.3536 0.01965 0.01211 -0.0194 0.9723 0.0085
-3.750 -0.3233 0.01807 0.01030 -0.0196 0.9704 0.0085
-3.500 -0.2924 0.01683 0.00891 -0.0202 0.9687 0.0085
-3.250 -0.2698 0.01588 0.00784 -0.0190 0.9642 0.0087
-3.000 -0.2422 0.01504 0.00680 -0.0189 0.9608 0.0090
-2.750 -0.2109 0.01444 0.00603 -0.0195 0.9582 0.0095
-2.500 -0.1773 0.01380 0.00521 -0.0206 0.9561 0.0131
-2.250 -0.1570 0.01284 0.00480 -0.0193 0.9505 0.1250
-2.000 -0.1481 0.01050 0.00468 -0.0165 0.9455 0.6158
-1.750 -0.0864 0.01011 0.00507 -0.0223 0.9491 0.8799
-1.500 -0.0287 0.01032 0.00511 -0.0281 0.9500 0.9252
-1.250 0.0169 0.01046 0.00513 -0.0315 0.9480 0.9482
-1.000 0.0677 0.01061 0.00516 -0.0361 0.9468 0.9676
-0.750 0.1206 0.01056 0.00499 -0.0414 0.9454 0.9757
-0.500 0.1653 0.01048 0.00484 -0.0449 0.9425 0.9813
-0.250 0.2071 0.01033 0.00465 -0.0479 0.9363 0.9864
0.000 0.2506 0.01015 0.00445 -0.0513 0.9313 0.9908
0.250 0.2913 0.00997 0.00426 -0.0540 0.9240 0.9958
0.500 0.3331 0.00973 0.00402 -0.0569 0.9168 0.9999
0.750 0.3555 0.00961 0.00391 -0.0557 0.9047 1.0000
1.000 0.3775 0.00950 0.00380 -0.0544 0.8914 1.0000
1.250 0.3992 0.00938 0.00369 -0.0529 0.8760 1.0000
1.500 0.4190 0.00929 0.00364 -0.0511 0.8554 1.0000
1.750 0.4411 0.00916 0.00351 -0.0497 0.8308 1.0000
2.000 0.4655 0.00898 0.00328 -0.0485 0.7970 1.0000
2.250 0.4897 0.00888 0.00303 -0.0472 0.7495 1.0000
2.500 0.5117 0.00899 0.00290 -0.0455 0.6907 1.0000
2.750 0.5319 0.00927 0.00299 -0.0438 0.6286 1.0000
3.000 0.5514 0.00964 0.00310 -0.0420 0.5677 1.0000
3.250 0.5704 0.01005 0.00327 -0.0403 0.5064 1.0000
3.500 0.5892 0.01050 0.00348 -0.0386 0.4472 1.0000
3.750 0.6082 0.01096 0.00373 -0.0370 0.3899 1.0000
4.000 0.6271 0.01145 0.00401 -0.0355 0.3346 1.0000
4.250 0.6463 0.01194 0.00437 -0.0340 0.2847 1.0000
4.500 0.6654 0.01245 0.00472 -0.0326 0.2364 1.0000
4.750 0.6845 0.01298 0.00509 -0.0312 0.1927 1.0000
5.000 0.7035 0.01354 0.00550 -0.0297 0.1511 1.0000
5.250 0.7221 0.01416 0.00596 -0.0282 0.1118 1.0000
5.500 0.7404 0.01482 0.00646 -0.0267 0.0777 1.0000
5.750 0.7592 0.01542 0.00702 -0.0252 0.0562 1.0000
6.000 0.7776 0.01610 0.00768 -0.0235 0.0416 1.0000
6.250 0.7957 0.01682 0.00849 -0.0217 0.0328 1.0000
6.500 0.8121 0.01773 0.00955 -0.0197 0.0261 1.0000
6.750 0.8308 0.01834 0.01024 -0.0182 0.0194 1.0000
7.000 0.8493 0.01896 0.01090 -0.0167 0.0124 1.0000
7.250 0.8649 0.01999 0.01199 -0.0147 0.0079 1.0000
7.500 0.8796 0.02114 0.01335 -0.0123 0.0062 1.0000
7.750 0.8943 0.02232 0.01468 -0.0101 0.0050 1.0000
8.000 0.9072 0.02375 0.01629 -0.0076 0.0044 1.0000
8.250 0.9169 0.02573 0.01852 -0.0048 0.0040 1.0000
8.500 0.9247 0.02827 0.02136 -0.0017 0.0038 1.0000
8.750 0.9342 0.03045 0.02386 0.0011 0.0037 1.0000
9.000 0.9412 0.03283 0.02659 0.0040 0.0037 1.0000
9.250 0.9441 0.03554 0.02968 0.0073 0.0036 1.0000
9.500 0.9430 0.03832 0.03282 0.0108 0.0036 1.0000
9.750 0.9365 0.04120 0.03603 0.0147 0.0036 1.0000
10.000 0.9251 0.04387 0.03897 0.0190 0.0036 1.0000
10.250 0.9105 0.04690 0.04227 0.0225 0.0036 1.0000
10.500 0.8967 0.05000 0.04559 0.0249 0.0036 1.0000
10.750 0.8790 0.05390 0.04971 0.0261 0.0036 1.0000
11.000 0.8596 0.05862 0.05464 0.0255 0.0036 1.0000
11.250 0.8420 0.06411 0.06030 0.0228 0.0036 1.0000
11.500 0.8262 0.07073 0.06706 0.0181 0.0037 1.0000
11.750 0.8079 0.08010 0.07656 0.0110 0.0037 1.0000
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Polar data table (+)
Polar graphs
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