MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 50,000 Max Cl/Cd: 31.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh26-il-50000-n5.txt Download as CSV file: xf-mh26-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4949 0.10455 0.09765 -0.0422 1.0000 0.0349
-9.750 -0.4975 0.10120 0.09435 -0.0416 1.0000 0.0344
-9.500 -0.5039 0.09732 0.09053 -0.0420 1.0000 0.0340
-9.250 -0.5130 0.09312 0.08639 -0.0428 1.0000 0.0335
-9.000 -0.5240 0.08924 0.08257 -0.0434 1.0000 0.0331
-8.750 -0.5395 0.08564 0.07900 -0.0429 1.0000 0.0327
-8.500 -0.5575 0.08262 0.07600 -0.0410 1.0000 0.0324
-8.250 -0.5774 0.08001 0.07340 -0.0378 1.0000 0.0321
-8.000 -0.5956 0.07687 0.07024 -0.0348 1.0000 0.0319
-7.750 -0.6081 0.07392 0.06723 -0.0319 1.0000 0.0314
-7.500 -0.6217 0.07046 0.06366 -0.0287 1.0000 0.0311
-7.250 -0.6306 0.06732 0.06038 -0.0256 1.0000 0.0306
-7.000 -0.6387 0.06389 0.05677 -0.0222 1.0000 0.0303
-6.750 -0.6438 0.06053 0.05317 -0.0189 1.0000 0.0300
-6.500 -0.6459 0.05722 0.04958 -0.0156 1.0000 0.0296
-6.250 -0.6458 0.05384 0.04587 -0.0122 1.0000 0.0295
-6.000 -0.6425 0.05065 0.04232 -0.0089 1.0000 0.0293
-5.750 -0.6362 0.04762 0.03889 -0.0058 1.0000 0.0292
-5.500 -0.6273 0.04466 0.03550 -0.0028 1.0000 0.0293
-5.250 -0.6152 0.04194 0.03224 -0.0001 1.0000 0.0294
-5.000 -0.6002 0.03943 0.02927 0.0023 1.0000 0.0301
-4.750 -0.5825 0.03727 0.02663 0.0044 1.0000 0.0324
-4.500 -0.5622 0.03544 0.02428 0.0064 1.0000 0.0346
-4.250 -0.5413 0.03332 0.02196 0.0077 1.0000 0.0375
-4.000 -0.5185 0.03166 0.02010 0.0090 1.0000 0.0401
-3.750 -0.4940 0.03018 0.01838 0.0102 1.0000 0.0437
-3.500 -0.4704 0.02890 0.01695 0.0112 1.0000 0.0528
-3.250 -0.4465 0.02774 0.01563 0.0122 1.0000 0.0644
-3.000 -0.4239 0.02646 0.01443 0.0132 1.0000 0.0970
-2.750 -0.1597 0.02578 0.01627 -0.0267 1.0000 1.0000
-2.500 -0.1500 0.02557 0.01581 -0.0241 1.0000 1.0000
-2.250 -0.1397 0.02541 0.01536 -0.0217 1.0000 1.0000
-2.000 -0.1290 0.02529 0.01504 -0.0193 1.0000 1.0000
-1.750 -0.1179 0.02522 0.01476 -0.0169 1.0000 1.0000
-1.500 -0.1066 0.02518 0.01453 -0.0145 1.0000 1.0000
-1.250 -0.0951 0.02517 0.01437 -0.0121 1.0000 1.0000
-1.000 -0.0835 0.02520 0.01424 -0.0098 1.0000 1.0000
-0.750 -0.0718 0.02526 0.01413 -0.0075 1.0000 1.0000
-0.500 -0.0600 0.02535 0.01410 -0.0053 1.0000 1.0000
-0.250 -0.0481 0.02547 0.01411 -0.0031 1.0000 1.0000
0.000 -0.0233 0.02574 0.01425 -0.0035 0.9962 1.0000
0.250 0.0137 0.02613 0.01451 -0.0064 0.9881 1.0000
0.500 0.0504 0.02656 0.01484 -0.0092 0.9798 1.0000
0.750 0.0878 0.02699 0.01521 -0.0120 0.9713 1.0000
1.000 0.1215 0.02729 0.01548 -0.0140 0.9613 1.0000
1.250 0.1556 0.02760 0.01577 -0.0161 0.9513 1.0000
1.500 0.1917 0.02793 0.01610 -0.0185 0.9416 1.0000
1.750 0.2278 0.02820 0.01639 -0.0208 0.9314 1.0000
2.000 0.2597 0.02835 0.01660 -0.0221 0.9193 1.0000
2.250 0.2916 0.02847 0.01679 -0.0234 0.9069 1.0000
2.500 0.3236 0.02853 0.01693 -0.0246 0.8940 1.0000
2.750 0.3550 0.02852 0.01702 -0.0256 0.8804 1.0000
3.000 0.3866 0.02844 0.01705 -0.0264 0.8662 1.0000
3.250 0.4188 0.02827 0.01708 -0.0273 0.8515 1.0000
3.500 0.4433 0.02809 0.01703 -0.0266 0.8338 1.0000
3.750 0.4715 0.02784 0.01695 -0.0264 0.8162 1.0000
4.000 0.5050 0.02742 0.01678 -0.0269 0.7993 1.0000
4.250 0.5329 0.02701 0.01656 -0.0263 0.7797 1.0000
4.500 0.5642 0.02642 0.01619 -0.0260 0.7596 1.0000
4.750 0.5936 0.02586 0.01585 -0.0253 0.7361 1.0000
5.000 0.6270 0.02522 0.01544 -0.0250 0.7086 1.0000
5.250 0.6693 0.02446 0.01497 -0.0261 0.6735 1.0000
5.500 0.7114 0.02394 0.01458 -0.0273 0.6246 1.0000
5.750 0.7500 0.02378 0.01438 -0.0280 0.5629 1.0000
6.000 0.7713 0.02412 0.01458 -0.0260 0.5019 1.0000
6.250 0.7847 0.02472 0.01498 -0.0229 0.4443 1.0000
6.500 0.7933 0.02546 0.01562 -0.0193 0.3908 1.0000
6.750 0.7995 0.02630 0.01625 -0.0154 0.3418 1.0000
7.000 0.8041 0.02720 0.01698 -0.0113 0.2956 1.0000
7.250 0.8087 0.02818 0.01779 -0.0074 0.2534 1.0000
7.500 0.8135 0.02925 0.01871 -0.0038 0.2141 1.0000
7.750 0.8190 0.03043 0.01972 -0.0004 0.1799 1.0000
8.000 0.8257 0.03172 0.02087 0.0027 0.1499 1.0000
8.250 0.8338 0.03312 0.02219 0.0056 0.1252 1.0000
8.500 0.8434 0.03456 0.02364 0.0082 0.1032 1.0000
8.750 0.8564 0.03620 0.02532 0.0104 0.0889 1.0000
9.000 0.8669 0.03774 0.02694 0.0128 0.0763 1.0000
9.250 0.8822 0.03958 0.02893 0.0145 0.0667 1.0000
9.500 0.9023 0.04185 0.03130 0.0154 0.0603 1.0000
9.750 0.9179 0.04410 0.03402 0.0172 0.0536 1.0000
10.000 0.9221 0.04582 0.03574 0.0200 0.0488 1.0000
10.250 0.9341 0.04889 0.03927 0.0220 0.0454 1.0000
10.500 0.9380 0.05190 0.04271 0.0249 0.0435 1.0000
10.750 0.9351 0.05491 0.04607 0.0283 0.0420 1.0000
11.000 0.9280 0.05751 0.04893 0.0318 0.0403 1.0000
11.250 0.9204 0.05990 0.05146 0.0348 0.0385 1.0000
11.500 0.9131 0.06267 0.05431 0.0372 0.0371 1.0000
11.750 0.8985 0.06603 0.05785 0.0397 0.0362 1.0000
12.000 0.8811 0.06961 0.06168 0.0417 0.0360 1.0000
12.250 0.8595 0.07376 0.06610 0.0427 0.0357 1.0000
12.500 0.8402 0.07823 0.07075 0.0427 0.0358 1.0000
12.750 0.8217 0.08325 0.07592 0.0417 0.0360 1.0000
13.000 0.8027 0.08884 0.08161 0.0397 0.0363 1.0000
13.250 0.7409 0.10526 0.09835 0.0289 0.0432 1.0000
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Polar data table (+)
Polar graphs
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