MH 81 13% (mh81-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 81 13% (mh81-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.85 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh81-il-1000000-n5.txt Download as CSV file: xf-mh81-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7671 0.04213 0.03922 -0.0168 0.6611 0.0048
-9.750 -0.7824 0.03628 0.03296 -0.0164 0.6518 0.0048
-9.250 -0.7717 0.02964 0.02563 -0.0145 0.6280 0.0049
-9.000 -0.7557 0.02773 0.02347 -0.0137 0.6158 0.0049
-8.750 -0.7406 0.02545 0.02087 -0.0127 0.6034 0.0049
-8.500 -0.7224 0.02358 0.01873 -0.0118 0.5916 0.0049
-8.250 -0.7021 0.02204 0.01694 -0.0110 0.5800 0.0049
-8.000 -0.6804 0.02068 0.01534 -0.0103 0.5678 0.0049
-7.750 -0.6573 0.01954 0.01400 -0.0096 0.5562 0.0049
-7.500 -0.6335 0.01851 0.01278 -0.0090 0.5452 0.0049
-7.250 -0.6090 0.01759 0.01167 -0.0084 0.5336 0.0049
-7.000 -0.5838 0.01679 0.01073 -0.0079 0.5228 0.0049
-6.750 -0.5583 0.01605 0.00983 -0.0074 0.5122 0.0049
-6.500 -0.5324 0.01540 0.00905 -0.0069 0.5014 0.0049
-6.250 -0.5063 0.01473 0.00826 -0.0065 0.4917 0.0049
-6.000 -0.4803 0.01404 0.00744 -0.0060 0.4812 0.0050
-5.750 -0.4538 0.01347 0.00676 -0.0056 0.4718 0.0050
-5.500 -0.4270 0.01296 0.00615 -0.0052 0.4627 0.0050
-5.250 -0.3999 0.01251 0.00561 -0.0048 0.4527 0.0051
-5.000 -0.3726 0.01211 0.00513 -0.0045 0.4439 0.0052
-4.750 -0.3450 0.01177 0.00472 -0.0042 0.4353 0.0053
-4.500 -0.3172 0.01147 0.00436 -0.0040 0.4278 0.0054
-4.250 -0.2892 0.01121 0.00404 -0.0037 0.4192 0.0055
-4.000 -0.2612 0.01099 0.00376 -0.0035 0.4108 0.0057
-3.750 -0.2330 0.01077 0.00349 -0.0033 0.4020 0.0059
-3.500 -0.2047 0.01059 0.00326 -0.0031 0.3949 0.0061
-3.250 -0.1764 0.01041 0.00304 -0.0030 0.3879 0.0064
-2.750 -0.1196 0.01010 0.00264 -0.0026 0.3740 0.0075
-2.500 -0.0911 0.00998 0.00248 -0.0025 0.3659 0.0084
-2.250 -0.0626 0.00987 0.00233 -0.0024 0.3594 0.0097
-2.000 -0.0340 0.00975 0.00220 -0.0023 0.3527 0.0122
-1.750 -0.0055 0.00965 0.00209 -0.0022 0.3467 0.0172
-1.500 0.0230 0.00953 0.00199 -0.0021 0.3414 0.0254
-1.250 0.0514 0.00941 0.00189 -0.0020 0.3349 0.0404
-1.000 0.0794 0.00919 0.00180 -0.0019 0.3290 0.0796
-0.750 0.1073 0.00896 0.00174 -0.0018 0.3231 0.1306
-0.500 0.1352 0.00876 0.00169 -0.0017 0.3174 0.1864
-0.250 0.1632 0.00856 0.00165 -0.0017 0.3130 0.2441
0.000 0.1904 0.00822 0.00162 -0.0016 0.3084 0.3457
0.250 0.2181 0.00802 0.00161 -0.0015 0.3031 0.4210
0.500 0.2457 0.00782 0.00160 -0.0014 0.2982 0.4983
0.750 0.2730 0.00759 0.00160 -0.0012 0.2938 0.5821
1.000 0.3001 0.00738 0.00162 -0.0009 0.2894 0.6642
1.250 0.3261 0.00715 0.00166 -0.0004 0.2851 0.7580
1.500 0.3519 0.00701 0.00173 0.0004 0.2819 0.8318
1.750 0.3787 0.00700 0.00179 0.0009 0.2781 0.8702
2.000 0.4058 0.00704 0.00186 0.0014 0.2738 0.8952
2.250 0.4323 0.00711 0.00194 0.0020 0.2696 0.9191
2.500 0.4587 0.00717 0.00201 0.0026 0.2668 0.9411
2.750 0.4859 0.00724 0.00208 0.0031 0.2640 0.9572
3.000 0.5157 0.00732 0.00215 0.0029 0.2605 0.9692
3.250 0.5492 0.00744 0.00223 0.0019 0.2562 0.9774
3.500 0.5826 0.00757 0.00231 0.0009 0.2526 0.9843
3.750 0.6190 0.00766 0.00239 -0.0008 0.2502 0.9874
4.000 0.6534 0.00776 0.00247 -0.0021 0.2473 0.9899
4.250 0.6858 0.00788 0.00255 -0.0030 0.2438 0.9921
4.500 0.7175 0.00802 0.00265 -0.0038 0.2401 0.9940
4.750 0.7503 0.00814 0.00275 -0.0048 0.2374 0.9954
5.000 0.7826 0.00824 0.00285 -0.0058 0.2353 0.9970
5.250 0.8146 0.00835 0.00295 -0.0067 0.2325 0.9986
5.500 0.8462 0.00849 0.00307 -0.0075 0.2292 1.0000
5.750 0.8710 0.00864 0.00321 -0.0069 0.2262 1.0000
6.000 0.8961 0.00880 0.00335 -0.0064 0.2235 1.0000
6.250 0.9217 0.00892 0.00348 -0.0059 0.2219 1.0000
6.500 0.9474 0.00905 0.00362 -0.0055 0.2197 1.0000
6.750 0.9732 0.00920 0.00377 -0.0052 0.2169 1.0000
7.000 0.9990 0.00937 0.00393 -0.0049 0.2139 1.0000
7.250 1.0250 0.00956 0.00411 -0.0046 0.2111 1.0000
7.500 1.0514 0.00973 0.00429 -0.0044 0.2089 1.0000
7.750 1.0780 0.00988 0.00445 -0.0042 0.2069 1.0000
8.000 1.1046 0.01005 0.00464 -0.0041 0.2041 1.0000
8.250 1.1312 0.01024 0.00483 -0.0040 0.2012 1.0000
8.500 1.1575 0.01046 0.00505 -0.0039 0.1984 1.0000
8.750 1.1839 0.01068 0.00528 -0.0038 0.1954 1.0000
9.000 1.2106 0.01086 0.00548 -0.0038 0.1931 1.0000
9.250 1.2371 0.01106 0.00571 -0.0037 0.1903 1.0000
9.500 1.2632 0.01130 0.00595 -0.0037 0.1870 1.0000
9.750 1.2889 0.01159 0.00623 -0.0036 0.1833 1.0000
10.000 1.3151 0.01181 0.00649 -0.0035 0.1808 1.0000
10.250 1.3410 0.01205 0.00675 -0.0035 0.1777 1.0000
10.500 1.3665 0.01233 0.00704 -0.0034 0.1739 1.0000
10.750 1.3912 0.01268 0.00739 -0.0032 0.1698 1.0000
11.000 1.4166 0.01293 0.00769 -0.0031 0.1671 1.0000
11.250 1.4415 0.01323 0.00801 -0.0030 0.1635 1.0000
11.500 1.4654 0.01360 0.00840 -0.0028 0.1594 1.0000
11.750 1.4892 0.01397 0.00879 -0.0026 0.1557 1.0000
12.000 1.5130 0.01431 0.00916 -0.0024 0.1521 1.0000
12.250 1.5355 0.01475 0.00961 -0.0021 0.1475 1.0000
12.500 1.5574 0.01521 0.01009 -0.0017 0.1436 1.0000
12.750 1.5794 0.01562 0.01054 -0.0013 0.1398 1.0000
13.000 1.5992 0.01617 0.01110 -0.0008 0.1350 1.0000
13.250 1.6183 0.01672 0.01168 -0.0001 0.1305 1.0000
13.500 1.6349 0.01739 0.01236 0.0007 0.1243 1.0000
13.750 1.6484 0.01818 0.01315 0.0019 0.1178 1.0000
14.000 1.6519 0.01922 0.01418 0.0042 0.1107 1.0000
14.250 1.6527 0.02041 0.01540 0.0064 0.1049 1.0000
14.500 1.6477 0.02237 0.01737 0.0079 0.0974 1.0000
14.750 1.6514 0.02404 0.01910 0.0084 0.0944 1.0000
15.000 1.6453 0.02678 0.02186 0.0086 0.0884 1.0000
15.250 1.6367 0.03000 0.02512 0.0084 0.0820 1.0000
15.500 1.6215 0.03410 0.02925 0.0077 0.0751 1.0000
15.750 1.6280 0.03606 0.03133 0.0074 0.0773 1.0000
16.000 1.6067 0.04110 0.03641 0.0061 0.0717 1.0000
16.250 1.5884 0.04593 0.04132 0.0049 0.0678 1.0000
16.500 1.5824 0.04947 0.04497 0.0039 0.0681 1.0000
16.750 1.5635 0.05460 0.05019 0.0022 0.0657 1.0000
17.000 1.5340 0.06134 0.05699 -0.0002 0.0621 1.0000
17.250 1.5115 0.06746 0.06320 -0.0025 0.0587 1.0000
17.500 1.5040 0.07167 0.06752 -0.0041 0.0595 1.0000
17.750 1.4808 0.07825 0.07419 -0.0069 0.0569 1.0000
18.000 1.4546 0.08543 0.08143 -0.0100 0.0540 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 81 13% (mh81-il)