MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 100,000 Max Cl/Cd: 47.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh26-il-100000-n5.txt Download as CSV file: xf-mh26-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5091 0.09358 0.08879 -0.0373 1.0000 0.0146
-9.250 -0.5198 0.08923 0.08450 -0.0383 1.0000 0.0144
-9.000 -0.5325 0.08478 0.08009 -0.0399 1.0000 0.0143
-8.750 -0.5499 0.08044 0.07577 -0.0408 1.0000 0.0141
-8.500 -0.5698 0.07716 0.07248 -0.0392 1.0000 0.0140
-8.250 -0.5922 0.07459 0.06990 -0.0358 1.0000 0.0138
-8.000 -0.6142 0.07159 0.06685 -0.0318 1.0000 0.0138
-7.750 -0.6275 0.06877 0.06395 -0.0286 1.0000 0.0136
-7.500 -0.6421 0.06511 0.06017 -0.0250 1.0000 0.0135
-7.250 -0.6509 0.06198 0.05691 -0.0216 1.0000 0.0132
-7.000 -0.6590 0.05840 0.05314 -0.0180 1.0000 0.0130
-6.750 -0.6639 0.05493 0.04944 -0.0144 1.0000 0.0128
-6.500 -0.6660 0.05154 0.04579 -0.0108 1.0000 0.0126
-6.250 -0.6646 0.04789 0.04180 -0.0074 0.9995 0.0125
-6.000 -0.6513 0.04393 0.03738 -0.0061 0.9963 0.0123
-5.750 -0.6354 0.04040 0.03335 -0.0046 0.9934 0.0121
-5.500 -0.6183 0.03719 0.02962 -0.0029 0.9902 0.0122
-5.250 -0.5975 0.03445 0.02637 -0.0016 0.9874 0.0121
-5.000 -0.5731 0.03225 0.02364 -0.0010 0.9849 0.0130
-4.750 -0.5454 0.03065 0.02153 -0.0006 0.9826 0.0151
-4.500 -0.5211 0.02896 0.01949 0.0002 0.9796 0.0162
-4.250 -0.4956 0.02705 0.01739 0.0007 0.9770 0.0173
-4.000 -0.4685 0.02573 0.01593 0.0008 0.9743 0.0185
-3.750 -0.4401 0.02463 0.01471 0.0007 0.9717 0.0204
-3.500 -0.4157 0.02371 0.01360 0.0015 0.9683 0.0236
-3.250 -0.3931 0.02288 0.01273 0.0022 0.9641 0.0299
-3.000 -0.3671 0.02197 0.01173 0.0027 0.9606 0.0488
-2.750 -0.3421 0.02057 0.01115 0.0027 0.9578 0.1787
-2.500 -0.3285 0.01879 0.01091 0.0048 0.9535 0.4888
-2.250 -0.2233 0.01983 0.01310 -0.0072 0.9629 0.9181
-2.000 -0.1609 0.02065 0.01355 -0.0136 0.9636 0.9487
-1.750 -0.0834 0.02128 0.01386 -0.0236 0.9668 0.9745
-1.500 -0.0263 0.02139 0.01375 -0.0302 0.9662 0.9863
-1.250 0.0233 0.02142 0.01358 -0.0353 0.9643 0.9943
-1.000 0.0710 0.02138 0.01340 -0.0402 0.9619 1.0000
-0.750 0.1067 0.02141 0.01332 -0.0425 0.9578 1.0000
-0.500 0.1310 0.02131 0.01313 -0.0424 0.9501 1.0000
0.000 0.1921 0.02120 0.01291 -0.0445 0.9372 1.0000
0.250 0.2284 0.02114 0.01281 -0.0467 0.9319 1.0000
0.500 0.2530 0.02102 0.01269 -0.0465 0.9231 1.0000
0.750 0.2916 0.02090 0.01256 -0.0490 0.9179 1.0000
1.000 0.3147 0.02075 0.01242 -0.0483 0.9078 1.0000
1.250 0.3438 0.02057 0.01228 -0.0487 0.8992 1.0000
1.500 0.3789 0.02033 0.01207 -0.0503 0.8918 1.0000
1.750 0.4020 0.02010 0.01189 -0.0495 0.8804 1.0000
2.000 0.4266 0.01985 0.01169 -0.0488 0.8689 1.0000
2.250 0.4514 0.01957 0.01147 -0.0481 0.8570 1.0000
2.500 0.4758 0.01926 0.01127 -0.0473 0.8441 1.0000
2.750 0.4991 0.01893 0.01102 -0.0462 0.8301 1.0000
3.000 0.5222 0.01856 0.01074 -0.0449 0.8151 1.0000
3.250 0.5487 0.01815 0.01042 -0.0442 0.7990 1.0000
3.500 0.5749 0.01778 0.01018 -0.0435 0.7790 1.0000
3.750 0.6143 0.01721 0.00971 -0.0451 0.7565 1.0000
4.000 0.6641 0.01664 0.00921 -0.0487 0.7208 1.0000
4.250 0.7276 0.01610 0.00864 -0.0550 0.6602 1.0000
4.500 0.7651 0.01617 0.00849 -0.0565 0.5906 1.0000
4.750 0.7868 0.01655 0.00863 -0.0551 0.5268 1.0000
5.000 0.8019 0.01706 0.00890 -0.0525 0.4686 1.0000
5.250 0.8138 0.01763 0.00925 -0.0495 0.4137 1.0000
5.500 0.8244 0.01823 0.00966 -0.0463 0.3630 1.0000
5.750 0.8340 0.01887 0.01011 -0.0429 0.3153 1.0000
6.000 0.8436 0.01952 0.01066 -0.0397 0.2713 1.0000
6.250 0.8527 0.02020 0.01119 -0.0364 0.2292 1.0000
6.500 0.8615 0.02093 0.01176 -0.0331 0.1908 1.0000
6.750 0.8707 0.02166 0.01237 -0.0299 0.1565 1.0000
7.000 0.8786 0.02247 0.01304 -0.0265 0.1255 1.0000
7.250 0.8869 0.02328 0.01377 -0.0231 0.1013 1.0000
7.500 0.8939 0.02413 0.01456 -0.0196 0.0818 1.0000
7.750 0.8998 0.02496 0.01536 -0.0158 0.0670 1.0000
8.000 0.9030 0.02588 0.01628 -0.0115 0.0587 1.0000
8.250 0.9073 0.02677 0.01728 -0.0073 0.0517 1.0000
8.500 0.9100 0.02782 0.01836 -0.0031 0.0457 1.0000
8.750 0.9162 0.02870 0.01934 0.0004 0.0397 1.0000
9.000 0.9176 0.03002 0.02074 0.0045 0.0364 1.0000
9.250 0.9256 0.03129 0.02224 0.0078 0.0337 1.0000
9.500 0.9342 0.03270 0.02381 0.0108 0.0309 1.0000
9.750 0.9390 0.03390 0.02509 0.0140 0.0276 1.0000
10.000 0.9452 0.03573 0.02706 0.0169 0.0247 1.0000
10.250 0.9548 0.03768 0.02931 0.0196 0.0225 1.0000
10.500 0.9591 0.03922 0.03106 0.0226 0.0204 1.0000
10.750 0.9590 0.04065 0.03260 0.0259 0.0185 1.0000
11.000 0.9556 0.04341 0.03547 0.0291 0.0168 1.0000
11.250 0.9549 0.04582 0.03822 0.0322 0.0162 1.0000
11.500 0.9506 0.04853 0.04126 0.0354 0.0158 1.0000
11.750 0.9415 0.05146 0.04453 0.0386 0.0152 1.0000
12.000 0.9306 0.05447 0.04782 0.0412 0.0149 1.0000
12.250 0.9157 0.05787 0.05151 0.0435 0.0143 1.0000
12.500 0.9002 0.06165 0.05552 0.0449 0.0145 1.0000
12.750 0.8838 0.06550 0.05960 0.0454 0.0139 1.0000
13.000 0.8639 0.07056 0.06488 0.0450 0.0146 1.0000
13.250 0.8430 0.07610 0.07062 0.0432 0.0144 1.0000
13.500 0.8215 0.08258 0.07727 0.0400 0.0144 1.0000
13.750 0.8012 0.08972 0.08454 0.0362 0.0152 1.0000
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Polar data table (+)
Polar graphs
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