MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 200,000 Max Cl/Cd: 57.81 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh26-il-200000-n5.txt Download as CSV file: xf-mh26-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 26 10.99%
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4744 0.12511 0.12150 -0.0320 1.0000 0.0158
-11.250 -0.4766 0.12144 0.11786 -0.0322 1.0000 0.0158
-11.000 -0.4790 0.11787 0.11432 -0.0325 1.0000 0.0158
-10.750 -0.4818 0.11427 0.11074 -0.0328 1.0000 0.0158
-9.750 -0.5085 0.09621 0.09280 -0.0328 1.0000 0.0087
-9.500 -0.5127 0.09083 0.08745 -0.0360 0.9987 0.0085
-9.250 -0.5170 0.08476 0.08141 -0.0407 0.9968 0.0083
-9.000 -0.5234 0.07791 0.07455 -0.0476 0.9947 0.0082
-8.750 -0.5366 0.07227 0.06885 -0.0510 0.9920 0.0081
-8.500 -0.5508 0.06811 0.06459 -0.0513 0.9884 0.0079
-8.250 -0.5619 0.06412 0.06048 -0.0505 0.9849 0.0078
-8.000 -0.5698 0.05937 0.05556 -0.0495 0.9813 0.0077
-7.750 -0.5739 0.05590 0.05192 -0.0473 0.9771 0.0075
-7.500 -0.5769 0.05120 0.04697 -0.0452 0.9736 0.0073
-7.250 -0.5708 0.04710 0.04256 -0.0440 0.9711 0.0070
-7.000 -0.5736 0.04355 0.03871 -0.0398 0.9667 0.0069
-6.750 -0.5699 0.03984 0.03463 -0.0364 0.9629 0.0067
-6.500 -0.5599 0.03605 0.03039 -0.0338 0.9601 0.0064
-6.250 -0.5447 0.03240 0.02619 -0.0317 0.9581 0.0063
-6.000 -0.5346 0.02988 0.02325 -0.0283 0.9547 0.0062
-5.750 -0.5196 0.02769 0.02065 -0.0256 0.9513 0.0061
-5.500 -0.4980 0.02580 0.01835 -0.0243 0.9491 0.0062
-5.250 -0.4729 0.02416 0.01642 -0.0237 0.9473 0.0062
-5.000 -0.4458 0.02277 0.01480 -0.0235 0.9459 0.0064
-4.750 -0.4178 0.02159 0.01344 -0.0236 0.9447 0.0068
-4.500 -0.4009 0.02076 0.01250 -0.0214 0.9410 0.0071
-4.250 -0.3812 0.01997 0.01159 -0.0197 0.9374 0.0077
-4.000 -0.3562 0.01931 0.01081 -0.0192 0.9347 0.0087
-3.750 -0.3289 0.01865 0.01011 -0.0194 0.9327 0.0121
-3.500 -0.2990 0.01806 0.00936 -0.0198 0.9312 0.0162
-3.250 -0.2859 0.01753 0.00878 -0.0167 0.9256 0.0239
-3.000 -0.2662 0.01658 0.00832 -0.0154 0.9220 0.1066
-2.750 -0.2440 0.01557 0.00799 -0.0149 0.9194 0.2566
-2.500 -0.2252 0.01439 0.00770 -0.0136 0.9172 0.4687
-2.250 -0.1959 0.01347 0.00824 -0.0131 0.9154 0.7936
-2.000 -0.1291 0.01407 0.00877 -0.0205 0.9178 0.8759
-1.750 -0.1061 0.01433 0.00894 -0.0191 0.9123 0.8997
-1.500 -0.0680 0.01467 0.00916 -0.0209 0.9097 0.9171
-1.250 -0.0138 0.01515 0.00951 -0.0260 0.9095 0.9317
-1.000 0.0330 0.01533 0.00959 -0.0299 0.9080 0.9398
-0.750 0.0759 0.01535 0.00952 -0.0331 0.9061 0.9448
-0.500 0.1239 0.01531 0.00940 -0.0374 0.9049 0.9478
-0.250 0.1456 0.01535 0.00940 -0.0361 0.8977 0.9563
0.000 0.1937 0.01524 0.00926 -0.0405 0.8952 0.9589
0.250 0.2401 0.01506 0.00906 -0.0445 0.8929 0.9614
0.500 0.2862 0.01481 0.00879 -0.0484 0.8909 0.9635
0.750 0.3050 0.01475 0.00874 -0.0465 0.8812 0.9700
1.000 0.3493 0.01439 0.00839 -0.0500 0.8781 0.9709
1.250 0.3785 0.01419 0.00823 -0.0505 0.8683 0.9740
1.500 0.4103 0.01392 0.00798 -0.0513 0.8598 0.9768
1.750 0.4425 0.01362 0.00771 -0.0522 0.8512 0.9794
2.250 0.4985 0.01314 0.00733 -0.0523 0.8224 0.9847
2.500 0.5358 0.01277 0.00701 -0.0542 0.8045 0.9856
2.750 0.5845 0.01227 0.00650 -0.0582 0.7796 0.9847
3.000 0.6345 0.01186 0.00597 -0.0624 0.7339 0.9832
3.250 0.6710 0.01185 0.00572 -0.0640 0.6751 0.9835
3.500 0.6979 0.01210 0.00570 -0.0639 0.6137 0.9851
3.750 0.7203 0.01246 0.00580 -0.0629 0.5547 0.9876
4.000 0.7400 0.01290 0.00602 -0.0616 0.4970 0.9904
4.250 0.7584 0.01338 0.00627 -0.0600 0.4410 0.9932
4.500 0.7789 0.01384 0.00652 -0.0590 0.3875 0.9954
4.750 0.7999 0.01433 0.00679 -0.0581 0.3345 0.9976
5.000 0.8217 0.01484 0.00712 -0.0575 0.2865 0.9998
5.250 0.8350 0.01533 0.00747 -0.0549 0.2474 1.0000
5.500 0.8469 0.01583 0.00783 -0.0521 0.2109 1.0000
5.750 0.8585 0.01636 0.00827 -0.0492 0.1766 1.0000
6.000 0.8698 0.01690 0.00868 -0.0464 0.1440 1.0000
6.250 0.8807 0.01746 0.00912 -0.0434 0.1148 1.0000
6.500 0.8919 0.01800 0.00958 -0.0405 0.0924 1.0000
6.750 0.9026 0.01853 0.01007 -0.0375 0.0748 1.0000
7.000 0.9126 0.01910 0.01060 -0.0343 0.0606 1.0000
7.250 0.9217 0.01967 0.01116 -0.0309 0.0489 1.0000
7.500 0.9291 0.02020 0.01171 -0.0272 0.0399 1.0000
7.750 0.9348 0.02077 0.01232 -0.0231 0.0344 1.0000
8.000 0.9408 0.02130 0.01295 -0.0192 0.0306 1.0000
8.250 0.9448 0.02199 0.01369 -0.0149 0.0275 1.0000
8.500 0.9477 0.02277 0.01456 -0.0104 0.0249 1.0000
8.750 0.9543 0.02338 0.01536 -0.0067 0.0224 1.0000
9.000 0.9609 0.02403 0.01609 -0.0032 0.0199 1.0000
9.250 0.9630 0.02502 0.01714 0.0010 0.0176 1.0000
9.500 0.9681 0.02590 0.01813 0.0047 0.0159 1.0000
9.750 0.9749 0.02672 0.01909 0.0080 0.0138 1.0000
10.000 0.9826 0.02741 0.01980 0.0108 0.0109 1.0000
10.250 0.9830 0.02881 0.02133 0.0148 0.0098 1.0000
10.500 0.9890 0.02986 0.02255 0.0179 0.0090 1.0000
10.750 0.9931 0.03114 0.02400 0.0211 0.0078 1.0000
11.000 0.9965 0.03241 0.02540 0.0242 0.0069 1.0000
11.250 0.9985 0.03388 0.02701 0.0273 0.0066 1.0000
11.500 0.9989 0.03554 0.02882 0.0304 0.0063 1.0000
11.750 0.9933 0.03784 0.03129 0.0337 0.0059 1.0000
12.000 0.9880 0.04033 0.03398 0.0368 0.0057 1.0000
12.250 0.9840 0.04274 0.03670 0.0394 0.0055 1.0000
12.500 0.9788 0.04525 0.03942 0.0417 0.0055 1.0000
12.750 0.9702 0.04825 0.04268 0.0437 0.0053 1.0000
13.000 0.9601 0.05149 0.04614 0.0452 0.0054 1.0000
13.250 0.9465 0.05537 0.05027 0.0461 0.0052 1.0000
13.500 0.9316 0.05971 0.05485 0.0461 0.0052 1.0000
13.750 0.9164 0.06444 0.05980 0.0452 0.0052 1.0000
14.000 0.9006 0.06977 0.06531 0.0434 0.0052 1.0000
14.250 0.8815 0.07630 0.07205 0.0404 0.0052 1.0000
14.500 0.8625 0.08351 0.07943 0.0365 0.0052 1.0000
14.750 0.8476 0.09042 0.08647 0.0326 0.0054 1.0000
15.000 0.8263 0.09946 0.09565 0.0273 0.0054 1.0000
15.250 0.8059 0.10874 0.10499 0.0222 0.0055 1.0000
15.500 0.7849 0.11867 0.11500 0.0170 0.0056 1.0000
15.750 0.7598 0.13019 0.12657 0.0115 0.0057 1.0000
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