MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 200,000 Max Cl/Cd: 71.2 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh26-il-200000.txt Download as CSV file: xf-mh26-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5473 0.09076 0.08747 -0.0413 1.0000 0.0352
-8.750 -0.5673 0.08794 0.08462 -0.0395 1.0000 0.0352
-8.500 -0.5891 0.08582 0.08248 -0.0358 1.0000 0.0352
-8.250 -0.6089 0.08359 0.08020 -0.0320 1.0000 0.0352
-8.000 -0.6264 0.08088 0.07740 -0.0285 1.0000 0.0353
-7.750 -0.6379 0.07823 0.07465 -0.0253 1.0000 0.0353
-7.500 -0.6603 0.07210 0.06843 -0.0221 1.0000 0.0358
-7.250 -0.6674 0.06748 0.06381 -0.0197 1.0000 0.0365
-7.000 -0.6685 0.06438 0.06073 -0.0173 1.0000 0.0373
-6.750 -0.6696 0.06171 0.05802 -0.0145 1.0000 0.0382
-6.500 -0.6700 0.05913 0.05536 -0.0117 1.0000 0.0392
-6.250 -0.6700 0.05635 0.05245 -0.0088 1.0000 0.0407
-6.000 -0.6683 0.05353 0.04945 -0.0058 1.0000 0.0427
-5.750 -0.6634 0.05366 0.04892 -0.0009 1.0000 0.0477
-5.500 -0.6679 0.04741 0.04243 0.0021 1.0000 0.0493
-5.250 -0.6580 0.04447 0.03951 0.0039 1.0000 0.0508
-5.000 -0.6475 0.04229 0.03726 0.0061 1.0000 0.0532
-4.250 -0.6041 0.03130 0.02478 0.0167 1.0000 0.0306
-4.000 -0.5718 0.02698 0.01970 0.0182 0.9974 0.0204
-3.500 -0.5005 0.02263 0.01450 0.0171 0.9895 0.0178
-3.250 -0.4658 0.02157 0.01330 0.0159 0.9855 0.0177
-3.000 -0.4326 0.02077 0.01246 0.0148 0.9810 0.0209
-2.750 -0.4020 0.02034 0.01193 0.0142 0.9753 0.0249
-2.500 -0.3692 0.01948 0.01101 0.0133 0.9714 0.0348
-2.250 -0.3630 0.01659 0.01003 0.0170 0.9645 0.3945
-2.000 -0.2320 0.01794 0.01326 -0.0002 0.9788 0.9613
-1.750 -0.1413 0.01901 0.01399 -0.0129 0.9832 0.9811
-1.500 -0.0553 0.01924 0.01399 -0.0252 0.9861 0.9971
-1.250 -0.0038 0.01945 0.01404 -0.0308 0.9834 1.0000
-1.000 0.0301 0.01932 0.01382 -0.0328 0.9760 1.0000
-0.750 0.0733 0.01944 0.01385 -0.0367 0.9713 1.0000
-0.500 0.1046 0.01932 0.01366 -0.0381 0.9633 1.0000
-0.250 0.1479 0.01936 0.01363 -0.0418 0.9586 1.0000
0.000 0.1789 0.01923 0.01346 -0.0429 0.9502 1.0000
0.250 0.2235 0.01917 0.01338 -0.0468 0.9456 1.0000
0.500 0.2542 0.01900 0.01319 -0.0477 0.9369 1.0000
0.750 0.3004 0.01882 0.01301 -0.0517 0.9323 1.0000
1.000 0.3310 0.01858 0.01279 -0.0526 0.9234 1.0000
1.250 0.3781 0.01828 0.01252 -0.0566 0.9190 1.0000
1.500 0.4092 0.01796 0.01222 -0.0573 0.9098 1.0000
1.750 0.4583 0.01750 0.01182 -0.0616 0.9056 1.0000
2.000 0.4889 0.01709 0.01146 -0.0621 0.8959 1.0000
2.250 0.5413 0.01644 0.01093 -0.0668 0.8919 1.0000
2.500 0.5716 0.01590 0.01047 -0.0670 0.8812 1.0000
2.750 0.6279 0.01498 0.00967 -0.0723 0.8767 1.0000
3.000 0.6582 0.01427 0.00907 -0.0722 0.8644 1.0000
3.250 0.6709 0.01383 0.00871 -0.0687 0.8457 1.0000
3.500 0.6978 0.01321 0.00818 -0.0678 0.8265 1.0000
3.750 0.7353 0.01250 0.00755 -0.0691 0.7998 1.0000
4.000 0.7992 0.01161 0.00660 -0.0756 0.7413 1.0000
4.250 0.8316 0.01168 0.00630 -0.0759 0.6604 1.0000
4.500 0.8451 0.01215 0.00644 -0.0728 0.5886 1.0000
4.750 0.8535 0.01274 0.00671 -0.0688 0.5219 1.0000
5.000 0.8607 0.01334 0.00703 -0.0647 0.4601 1.0000
5.250 0.8672 0.01396 0.00739 -0.0607 0.4019 1.0000
5.500 0.8739 0.01459 0.00777 -0.0567 0.3472 1.0000
5.750 0.8803 0.01525 0.00824 -0.0527 0.2934 1.0000
6.000 0.8870 0.01593 0.00868 -0.0489 0.2433 1.0000
6.250 0.8940 0.01663 0.00915 -0.0452 0.1954 1.0000
6.500 0.9011 0.01736 0.00968 -0.0415 0.1544 1.0000
6.750 0.9077 0.01814 0.01028 -0.0377 0.1195 1.0000
7.000 0.9126 0.01903 0.01102 -0.0335 0.0908 1.0000
7.250 0.9144 0.01999 0.01183 -0.0288 0.0721 1.0000
7.500 0.9161 0.02085 0.01266 -0.0239 0.0595 1.0000
7.750 0.9210 0.02154 0.01342 -0.0196 0.0519 1.0000
8.000 0.9223 0.02274 0.01462 -0.0148 0.0470 1.0000
8.250 0.9309 0.02358 0.01558 -0.0112 0.0428 1.0000
8.500 0.9373 0.02473 0.01672 -0.0076 0.0377 1.0000
8.750 0.9526 0.02624 0.01844 -0.0054 0.0341 1.0000
9.000 0.9604 0.02705 0.01936 -0.0020 0.0302 1.0000
9.250 0.9775 0.02962 0.02205 -0.0007 0.0251 1.0000
9.500 0.9855 0.03067 0.02331 0.0029 0.0227 1.0000
9.750 0.9827 0.03097 0.02366 0.0078 0.0197 1.0000
10.000 0.9947 0.03568 0.02869 0.0095 0.0167 1.0000
10.250 0.9956 0.03754 0.03084 0.0137 0.0164 1.0000
10.500 0.9932 0.03964 0.03322 0.0182 0.0161 1.0000
10.750 0.9860 0.04189 0.03577 0.0232 0.0158 1.0000
11.000 0.9760 0.04428 0.03845 0.0282 0.0156 1.0000
11.250 0.9636 0.04693 0.04137 0.0328 0.0156 1.0000
11.500 0.9487 0.04978 0.04447 0.0371 0.0157 1.0000
11.750 0.9315 0.05280 0.04774 0.0410 0.0157 1.0000
12.000 0.9143 0.05601 0.05116 0.0439 0.0158 1.0000
12.250 0.8928 0.05984 0.05521 0.0462 0.0159 1.0000
12.500 0.8743 0.06376 0.05930 0.0473 0.0161 1.0000
12.750 0.8531 0.06829 0.06401 0.0473 0.0161 1.0000
13.000 0.8322 0.07358 0.06944 0.0462 0.0164 1.0000
13.250 0.8098 0.07961 0.07562 0.0436 0.0164 1.0000
13.500 0.7877 0.08656 0.08270 0.0399 0.0166 1.0000
14.250 0.5982 0.11281 0.10959 0.0250 0.0214 1.0000
14.500 0.5699 0.12106 0.11777 0.0212 0.0236 1.0000
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Polar data table (+)
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