MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 500,000 Max Cl/Cd: 77.84 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh26-il-500000.txt Download as CSV file: xf-mh26-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5118 0.08406 0.08198 -0.0414 0.9953 0.0134
-8.750 -0.5210 0.07697 0.07488 -0.0493 0.9930 0.0133
-8.500 -0.5369 0.07239 0.07024 -0.0509 0.9900 0.0131
-8.250 -0.5506 0.06855 0.06631 -0.0507 0.9864 0.0131
-8.000 -0.5527 0.06314 0.06076 -0.0522 0.9838 0.0135
-7.750 -0.5598 0.05976 0.05726 -0.0498 0.9794 0.0133
-7.500 -0.5605 0.05536 0.05268 -0.0480 0.9755 0.0142
-7.250 -0.5470 0.05188 0.04896 -0.0473 0.9731 0.0151
-7.000 -0.5288 0.04933 0.04611 -0.0468 0.9713 0.0157
-4.750 -0.4082 0.02190 0.01587 -0.0268 0.9449 0.0091
-4.500 -0.3941 0.01948 0.01324 -0.0237 0.9408 0.0081
-4.250 -0.3728 0.01806 0.01166 -0.0221 0.9375 0.0077
-4.000 -0.3461 0.01692 0.01039 -0.0216 0.9353 0.0076
-3.750 -0.3176 0.01600 0.00934 -0.0217 0.9336 0.0077
-3.500 -0.2864 0.01527 0.00851 -0.0223 0.9323 0.0085
-3.250 -0.2523 0.01477 0.00794 -0.0236 0.9313 0.0090
-2.250 -0.2075 0.01051 0.00637 -0.0105 0.9120 0.6656
-2.000 -0.1812 0.01003 0.00662 -0.0094 0.9095 0.8574
-1.750 -0.1397 0.01037 0.00697 -0.0116 0.9085 0.9100
-1.500 -0.0983 0.01062 0.00714 -0.0140 0.9075 0.9242
-1.250 -0.0524 0.01085 0.00730 -0.0175 0.9070 0.9322
-1.000 0.0082 0.01120 0.00757 -0.0244 0.9076 0.9361
-0.750 0.0567 0.01139 0.00770 -0.0285 0.9072 0.9433
-0.500 0.1290 0.01162 0.00788 -0.0380 0.9088 0.9448
-0.250 0.1841 0.01154 0.00776 -0.0438 0.9089 0.9456
0.000 0.2353 0.01137 0.00757 -0.0488 0.9083 0.9465
0.250 0.2845 0.01114 0.00733 -0.0534 0.9073 0.9477
0.500 0.3321 0.01090 0.00707 -0.0576 0.9062 0.9493
0.750 0.3780 0.01061 0.00679 -0.0614 0.9047 0.9515
1.000 0.3995 0.01054 0.00674 -0.0599 0.8972 0.9575
1.250 0.4443 0.01021 0.00642 -0.0635 0.8939 0.9586
1.500 0.4888 0.00983 0.00605 -0.0670 0.8904 0.9597
1.750 0.5188 0.00965 0.00590 -0.0674 0.8807 0.9630
2.000 0.5446 0.00946 0.00576 -0.0668 0.8696 0.9672
2.250 0.5702 0.00928 0.00560 -0.0663 0.8557 0.9707
2.500 0.6072 0.00896 0.00529 -0.0682 0.8368 0.9721
2.750 0.6438 0.00870 0.00497 -0.0700 0.8023 0.9733
3.000 0.6764 0.00869 0.00471 -0.0709 0.7461 0.9749
3.250 0.6987 0.00899 0.00471 -0.0697 0.6794 0.9780
3.500 0.7107 0.00948 0.00493 -0.0664 0.6214 0.9826
3.750 0.7357 0.00974 0.00492 -0.0662 0.5555 0.9845
4.000 0.7589 0.01010 0.00503 -0.0657 0.4924 0.9868
4.250 0.7808 0.01051 0.00518 -0.0649 0.4317 0.9894
4.500 0.8018 0.01093 0.00537 -0.0639 0.3757 0.9921
4.750 0.8232 0.01139 0.00559 -0.0631 0.3196 0.9943
5.000 0.8479 0.01188 0.00578 -0.0631 0.2556 0.9961
5.250 0.8727 0.01231 0.00600 -0.0631 0.2084 0.9979
5.500 0.8977 0.01277 0.00630 -0.0631 0.1659 0.9995
5.750 0.9151 0.01325 0.00662 -0.0615 0.1297 1.0000
6.000 0.9289 0.01370 0.00696 -0.0590 0.1033 1.0000
6.250 0.9421 0.01419 0.00734 -0.0564 0.0786 1.0000
6.500 0.9544 0.01471 0.00777 -0.0536 0.0579 1.0000
6.750 0.9659 0.01526 0.00826 -0.0507 0.0425 1.0000
7.000 0.9766 0.01584 0.00885 -0.0474 0.0332 1.0000
7.250 0.9858 0.01646 0.00947 -0.0439 0.0276 1.0000
7.500 0.9953 0.01698 0.01007 -0.0405 0.0246 1.0000
7.750 1.0065 0.01730 0.01044 -0.0375 0.0218 1.0000
8.000 1.0113 0.01779 0.01097 -0.0332 0.0182 1.0000
8.250 1.0116 0.01839 0.01167 -0.0280 0.0164 1.0000
8.500 1.0183 0.01871 0.01206 -0.0241 0.0150 1.0000
8.750 1.0251 0.01907 0.01247 -0.0203 0.0128 1.0000
9.000 1.0174 0.02031 0.01381 -0.0138 0.0099 1.0000
9.250 1.0248 0.02073 0.01430 -0.0101 0.0082 1.0000
9.500 1.0309 0.02123 0.01485 -0.0064 0.0076 1.0000
9.750 1.0304 0.02216 0.01582 -0.0017 0.0060 1.0000
10.000 1.0224 0.02383 0.01768 0.0044 0.0056 1.0000
10.250 1.0342 0.02397 0.01787 0.0069 0.0051 1.0000
10.500 1.0408 0.02458 0.01856 0.0102 0.0047 1.0000
10.750 1.0437 0.02555 0.01965 0.0140 0.0044 1.0000
11.000 1.0451 0.02672 0.02095 0.0179 0.0041 1.0000
11.250 1.0484 0.02778 0.02212 0.0213 0.0039 1.0000
11.500 1.0550 0.02852 0.02294 0.0240 0.0036 1.0000
11.750 1.0532 0.03011 0.02465 0.0276 0.0033 1.0000
12.000 1.0517 0.03183 0.02655 0.0310 0.0033 1.0000
12.250 1.0308 0.03564 0.03069 0.0360 0.0031 1.0000
12.500 1.0260 0.03784 0.03307 0.0389 0.0031 1.0000
12.750 1.0153 0.04071 0.03617 0.0418 0.0030 1.0000
13.000 1.0153 0.04247 0.03809 0.0435 0.0029 1.0000
13.250 1.0061 0.04541 0.04124 0.0453 0.0028 1.0000
13.500 0.9839 0.05012 0.04619 0.0467 0.0029 1.0000
13.750 0.9805 0.05285 0.04909 0.0470 0.0026 1.0000
14.000 0.9592 0.05825 0.05469 0.0464 0.0028 1.0000
14.250 0.9436 0.06350 0.06014 0.0448 0.0028 1.0000
14.500 0.9248 0.06982 0.06663 0.0421 0.0028 1.0000
14.750 0.8990 0.07793 0.07489 0.0381 0.0030 1.0000
15.000 0.8852 0.08477 0.08189 0.0342 0.0029 1.0000
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Polar data table (+)
Polar graphs
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