MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.15 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh26-il-1000000-n5.txt Download as CSV file: xf-mh26-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4543 0.03589 0.03320 -0.0913 0.9468 0.0024
-8.250 -0.4652 0.03178 0.02878 -0.0862 0.9438 0.0023
-8.000 -0.4783 0.02697 0.02355 -0.0798 0.9404 0.0022
-7.750 -0.4719 0.02461 0.02092 -0.0764 0.9379 0.0022
-7.500 -0.4696 0.02100 0.01685 -0.0718 0.9355 0.0021
-7.250 -0.4548 0.01922 0.01480 -0.0696 0.9340 0.0020
-7.000 -0.4385 0.01720 0.01246 -0.0674 0.9327 0.0020
-6.750 -0.4188 0.01570 0.01073 -0.0659 0.9315 0.0019
-6.500 -0.3977 0.01452 0.00935 -0.0647 0.9304 0.0019
-6.250 -0.3775 0.01344 0.00809 -0.0633 0.9290 0.0019
-6.000 -0.3570 0.01263 0.00717 -0.0619 0.9274 0.0019
-5.750 -0.3362 0.01198 0.00642 -0.0606 0.9257 0.0019
-5.500 -0.3148 0.01141 0.00576 -0.0593 0.9240 0.0019
-5.250 -0.2926 0.01093 0.00522 -0.0583 0.9224 0.0019
-5.000 -0.2699 0.01048 0.00469 -0.0573 0.9208 0.0020
-4.750 -0.2463 0.01008 0.00422 -0.0565 0.9194 0.0020
-4.500 -0.2219 0.00976 0.00384 -0.0558 0.9182 0.0021
-4.250 -0.1979 0.00949 0.00351 -0.0551 0.9165 0.0023
-4.000 -0.1751 0.00928 0.00326 -0.0541 0.9138 0.0024
-3.750 -0.1512 0.00904 0.00300 -0.0533 0.9111 0.0032
-3.500 -0.1264 0.00881 0.00276 -0.0528 0.9086 0.0059
-3.250 -0.1012 0.00856 0.00255 -0.0523 0.9063 0.0156
-3.000 -0.0768 0.00821 0.00232 -0.0518 0.9041 0.0473
-2.750 -0.0564 0.00786 0.00218 -0.0504 0.9006 0.1028
-2.500 -0.0373 0.00735 0.00202 -0.0488 0.8968 0.1969
-2.250 -0.0172 0.00685 0.00184 -0.0475 0.8933 0.2951
-2.000 0.0033 0.00634 0.00168 -0.0462 0.8905 0.3998
-1.750 0.0202 0.00599 0.00161 -0.0440 0.8855 0.4818
-1.500 0.0403 0.00569 0.00149 -0.0425 0.8808 0.5447
-1.250 0.0574 0.00526 0.00136 -0.0402 0.8764 0.6371
-1.000 0.0703 0.00490 0.00130 -0.0370 0.8696 0.7208
-0.750 0.0878 0.00455 0.00126 -0.0346 0.8636 0.8082
-0.500 0.1108 0.00449 0.00132 -0.0334 0.8551 0.8551
-0.250 0.1371 0.00448 0.00133 -0.0329 0.8453 0.8782
0.000 0.1637 0.00449 0.00132 -0.0326 0.8319 0.8918
0.250 0.1894 0.00451 0.00127 -0.0320 0.8125 0.9004
0.500 0.2150 0.00461 0.00125 -0.0315 0.7861 0.9051
0.750 0.2369 0.00477 0.00128 -0.0302 0.7544 0.9102
1.000 0.2545 0.00494 0.00130 -0.0279 0.7207 0.9159
1.250 0.2748 0.00518 0.00141 -0.0263 0.6858 0.9201
1.500 0.2905 0.00542 0.00151 -0.0236 0.6500 0.9269
1.750 0.3088 0.00570 0.00167 -0.0215 0.6156 0.9330
2.000 0.3263 0.00597 0.00182 -0.0193 0.5819 0.9391
2.250 0.3411 0.00619 0.00191 -0.0165 0.5468 0.9439
2.500 0.3618 0.00646 0.00203 -0.0151 0.5095 0.9462
2.750 0.3823 0.00668 0.00213 -0.0137 0.4776 0.9486
3.000 0.4003 0.00689 0.00223 -0.0117 0.4440 0.9515
3.250 0.4152 0.00706 0.00229 -0.0091 0.4145 0.9551
3.500 0.4350 0.00727 0.00239 -0.0076 0.3848 0.9574
3.750 0.4581 0.00754 0.00253 -0.0069 0.3499 0.9588
4.000 0.4814 0.00781 0.00269 -0.0063 0.3177 0.9604
4.250 0.5043 0.00809 0.00285 -0.0055 0.2861 0.9622
4.500 0.5268 0.00835 0.00300 -0.0047 0.2591 0.9645
4.750 0.5460 0.00862 0.00316 -0.0032 0.2289 0.9673
5.000 0.5644 0.00884 0.00330 -0.0015 0.2062 0.9701
5.250 0.5902 0.00916 0.00353 -0.0015 0.1775 0.9711
5.500 0.6160 0.00951 0.00376 -0.0015 0.1498 0.9722
5.750 0.6416 0.00988 0.00401 -0.0016 0.1218 0.9733
6.000 0.6675 0.01025 0.00428 -0.0017 0.0985 0.9745
6.250 0.6931 0.01060 0.00455 -0.0017 0.0779 0.9758
6.500 0.7178 0.01098 0.00484 -0.0015 0.0602 0.9772
7.000 0.7647 0.01161 0.00543 -0.0006 0.0393 0.9807
7.250 0.7859 0.01191 0.00572 0.0004 0.0317 0.9827
7.500 0.8130 0.01229 0.00608 -0.0001 0.0238 0.9833
7.750 0.8394 0.01271 0.00647 -0.0004 0.0171 0.9839
8.000 0.8657 0.01310 0.00685 -0.0007 0.0135 0.9846
8.250 0.8918 0.01352 0.00727 -0.0009 0.0106 0.9854
8.500 0.9179 0.01388 0.00766 -0.0012 0.0089 0.9863
8.750 0.9422 0.01436 0.00815 -0.0012 0.0060 0.9874
9.000 0.9667 0.01477 0.00858 -0.0011 0.0046 0.9885
9.250 0.9892 0.01528 0.00910 -0.0008 0.0028 0.9898
9.500 1.0117 0.01573 0.00959 -0.0004 0.0024 0.9912
9.750 1.0318 0.01632 0.01021 0.0005 0.0015 0.9927
10.000 1.0517 0.01691 0.01088 0.0013 0.0012 0.9941
10.250 1.0746 0.01744 0.01147 0.0015 0.0011 0.9952
10.500 1.0967 0.01799 0.01208 0.0017 0.0010 0.9963
10.750 1.1176 0.01868 0.01287 0.0022 0.0008 0.9976
11.000 1.1375 0.01944 0.01372 0.0027 0.0008 0.9988
11.250 1.1573 0.02018 0.01454 0.0032 0.0007 0.9997
11.500 1.1664 0.02091 0.01536 0.0060 0.0006 1.0000
11.750 1.1673 0.02180 0.01636 0.0103 0.0005 1.0000
12.000 1.1727 0.02249 0.01713 0.0137 0.0005 1.0000
12.250 1.1788 0.02319 0.01792 0.0168 0.0005 1.0000
12.500 1.1857 0.02394 0.01874 0.0197 0.0005 1.0000
12.750 1.1904 0.02492 0.01983 0.0227 0.0005 1.0000
13.000 1.1999 0.02561 0.02057 0.0249 0.0004 1.0000
13.250 1.2038 0.02676 0.02184 0.0277 0.0004 1.0000
13.500 1.2061 0.02808 0.02329 0.0305 0.0004 1.0000
13.750 1.2129 0.02910 0.02440 0.0325 0.0003 1.0000
14.000 1.2137 0.03063 0.02605 0.0351 0.0004 1.0000
14.250 1.2146 0.03221 0.02776 0.0374 0.0004 1.0000
14.500 1.2138 0.03400 0.02968 0.0395 0.0004 1.0000
14.750 1.2155 0.03567 0.03145 0.0412 0.0004 1.0000
15.000 1.2094 0.03816 0.03410 0.0430 0.0003 1.0000
15.250 1.2065 0.04050 0.03655 0.0443 0.0003 1.0000
15.500 1.1993 0.04348 0.03968 0.0452 0.0003 1.0000
15.750 1.1861 0.04740 0.04379 0.0456 0.0003 1.0000
16.000 1.1814 0.05063 0.04712 0.0454 0.0003 1.0000
16.250 1.1691 0.05511 0.05176 0.0445 0.0003 1.0000
16.500 1.1571 0.05994 0.05673 0.0430 0.0003 1.0000
16.750 1.1431 0.06545 0.06238 0.0408 0.0003 1.0000
17.000 1.1213 0.07265 0.06975 0.0374 0.0003 1.0000
17.250 1.0986 0.08048 0.07774 0.0334 0.0003 1.0000
17.500 1.0750 0.08879 0.08618 0.0292 0.0003 1.0000
17.750 1.0357 0.10050 0.09807 0.0234 0.0003 1.0000
18.000 1.0181 0.10795 0.10560 0.0200 0.0003 1.0000
18.250 0.9579 0.12471 0.12255 0.0121 0.0003 1.0000
18.500 0.9287 0.13521 0.13314 0.0072 0.0004 1.0000
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Polar data table (+)
Polar graphs
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