MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 500,000 Max Cl/Cd: 96.41 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh18-il-500000-n5.txt Download as CSV file: xf-mh18-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4690 0.08092 0.07832 -0.0225 0.7935 0.0031
-9.000 -0.4793 0.07534 0.07275 -0.0257 0.7866 0.0031
-8.750 -0.4898 0.07037 0.06778 -0.0292 0.7795 0.0029
-8.500 -0.5161 0.06367 0.06107 -0.0333 0.7717 0.0029
-8.250 -0.5325 0.05665 0.05391 -0.0359 0.7659 0.0028
-8.000 -0.5683 0.04235 0.03920 -0.0367 0.7608 0.0028
-7.750 -0.5972 0.02985 0.02573 -0.0327 0.7559 0.0028
-7.250 -0.5732 0.02334 0.01823 -0.0291 0.7470 0.0031
-7.000 -0.5543 0.02139 0.01591 -0.0278 0.7423 0.0032
-6.750 -0.5332 0.01991 0.01412 -0.0268 0.7381 0.0034
-6.500 -0.5107 0.01863 0.01259 -0.0260 0.7338 0.0035
-6.250 -0.4871 0.01759 0.01134 -0.0253 0.7296 0.0036
-6.000 -0.4631 0.01668 0.01022 -0.0246 0.7259 0.0037
-5.750 -0.4407 0.01540 0.00874 -0.0237 0.7224 0.0041
-5.500 -0.4155 0.01481 0.00807 -0.0234 0.7184 0.0045
-5.250 -0.3897 0.01435 0.00751 -0.0231 0.7144 0.0050
-5.000 -0.3645 0.01377 0.00681 -0.0226 0.7110 0.0053
-4.750 -0.3393 0.01312 0.00604 -0.0221 0.7077 0.0055
-4.500 -0.3137 0.01255 0.00538 -0.0216 0.7042 0.0057
-4.250 -0.2877 0.01208 0.00479 -0.0212 0.7007 0.0060
-4.000 -0.2615 0.01169 0.00429 -0.0208 0.6975 0.0065
-3.750 -0.2354 0.01122 0.00375 -0.0203 0.6945 0.0087
-3.500 -0.2089 0.01086 0.00336 -0.0201 0.6911 0.0157
-3.250 -0.1822 0.01057 0.00309 -0.0198 0.6878 0.0278
-3.000 -0.1565 0.01019 0.00285 -0.0196 0.6847 0.0595
-2.750 -0.1302 0.00990 0.00266 -0.0194 0.6819 0.0902
-2.250 -0.0764 0.00945 0.00234 -0.0192 0.6749 0.1440
-2.000 -0.0500 0.00919 0.00219 -0.0190 0.6714 0.1873
-1.750 -0.0238 0.00893 0.00206 -0.0188 0.6679 0.2364
-1.500 0.0025 0.00867 0.00196 -0.0186 0.6637 0.2887
-1.250 0.0284 0.00840 0.00186 -0.0183 0.6597 0.3504
-1.000 0.0532 0.00807 0.00175 -0.0179 0.6561 0.4336
-0.750 0.0763 0.00763 0.00169 -0.0171 0.6522 0.5453
-0.500 0.0974 0.00716 0.00163 -0.0157 0.6480 0.6647
-0.250 0.1181 0.00670 0.00160 -0.0140 0.6442 0.7881
0.000 0.1821 0.00651 0.00172 -0.0216 0.6403 0.9078
0.250 0.2392 0.00663 0.00181 -0.0278 0.6355 0.9343
0.500 0.2729 0.00674 0.00187 -0.0290 0.6312 0.9491
0.750 0.3036 0.00684 0.00192 -0.0296 0.6271 0.9610
1.000 0.3345 0.00693 0.00199 -0.0302 0.6221 0.9704
1.250 0.3727 0.00703 0.00205 -0.0325 0.6171 0.9783
1.500 0.4168 0.00713 0.00212 -0.0360 0.6117 0.9859
1.750 0.4584 0.00718 0.00215 -0.0391 0.6056 0.9915
2.000 0.4950 0.00722 0.00216 -0.0411 0.5998 0.9947
2.250 0.5323 0.00719 0.00215 -0.0433 0.5925 0.9974
2.500 0.5681 0.00720 0.00213 -0.0452 0.5853 0.9997
2.750 0.5955 0.00723 0.00216 -0.0453 0.5769 1.0000
3.000 0.6215 0.00727 0.00219 -0.0451 0.5681 1.0000
3.250 0.6475 0.00732 0.00225 -0.0448 0.5575 1.0000
3.500 0.6734 0.00739 0.00230 -0.0446 0.5446 1.0000
3.750 0.6993 0.00748 0.00236 -0.0443 0.5292 1.0000
4.000 0.7249 0.00761 0.00244 -0.0441 0.5086 1.0000
4.250 0.7502 0.00780 0.00257 -0.0438 0.4856 1.0000
4.500 0.7751 0.00804 0.00272 -0.0435 0.4602 1.0000
4.750 0.7997 0.00832 0.00291 -0.0432 0.4358 1.0000
5.000 0.8242 0.00861 0.00313 -0.0428 0.4119 1.0000
5.250 0.8483 0.00891 0.00337 -0.0424 0.3886 1.0000
5.500 0.8720 0.00926 0.00366 -0.0419 0.3643 1.0000
5.750 0.8952 0.00963 0.00395 -0.0414 0.3393 1.0000
6.000 0.9177 0.01005 0.00428 -0.0408 0.3112 1.0000
6.250 0.9382 0.01063 0.00468 -0.0400 0.2709 1.0000
6.500 0.9580 0.01125 0.00512 -0.0390 0.2312 1.0000
6.750 0.9771 0.01186 0.00558 -0.0379 0.1953 1.0000
7.000 0.9949 0.01253 0.00612 -0.0367 0.1611 1.0000
7.250 1.0114 0.01326 0.00668 -0.0352 0.1268 1.0000
7.500 1.0252 0.01412 0.00733 -0.0333 0.0898 1.0000
7.750 1.0374 0.01501 0.00804 -0.0312 0.0585 1.0000
8.000 1.0460 0.01605 0.00886 -0.0286 0.0284 1.0000
8.250 1.0572 0.01682 0.00956 -0.0262 0.0158 1.0000
8.500 1.0693 0.01749 0.01022 -0.0240 0.0108 1.0000
8.750 1.0785 0.01821 0.01093 -0.0213 0.0062 1.0000
9.000 1.0837 0.01882 0.01159 -0.0179 0.0047 1.0000
9.250 1.0887 0.01957 0.01237 -0.0147 0.0034 1.0000
9.500 1.0958 0.02039 0.01328 -0.0121 0.0026 1.0000
9.750 1.1035 0.02129 0.01424 -0.0098 0.0021 1.0000
10.000 1.1093 0.02242 0.01546 -0.0074 0.0018 1.0000
10.250 1.1188 0.02337 0.01649 -0.0056 0.0017 1.0000
10.500 1.1256 0.02457 0.01780 -0.0037 0.0014 1.0000
10.750 1.1336 0.02576 0.01907 -0.0020 0.0014 1.0000
11.000 1.1410 0.02702 0.02044 -0.0005 0.0013 1.0000
11.250 1.1481 0.02838 0.02189 0.0010 0.0013 1.0000
11.500 1.1534 0.02992 0.02353 0.0025 0.0012 1.0000
11.750 1.1579 0.03158 0.02529 0.0038 0.0012 1.0000
12.000 1.1632 0.03323 0.02704 0.0050 0.0011 1.0000
12.250 1.1660 0.03515 0.02906 0.0062 0.0011 1.0000
12.500 1.1682 0.03718 0.03120 0.0073 0.0010 1.0000
12.750 1.1708 0.03922 0.03338 0.0081 0.0010 1.0000
13.000 1.1703 0.04164 0.03592 0.0090 0.0010 1.0000
13.250 1.1693 0.04418 0.03858 0.0097 0.0010 1.0000
13.500 1.1692 0.04671 0.04123 0.0102 0.0010 1.0000
13.750 1.1683 0.04943 0.04407 0.0106 0.0010 1.0000
14.000 1.1643 0.05263 0.04740 0.0108 0.0009 1.0000
14.250 1.1612 0.05584 0.05074 0.0107 0.0009 1.0000
14.500 1.1581 0.05917 0.05420 0.0105 0.0009 1.0000
14.750 1.1502 0.06328 0.05846 0.0100 0.0009 1.0000
15.000 1.1447 0.06721 0.06253 0.0093 0.0009 1.0000
15.250 1.1403 0.07114 0.06659 0.0083 0.0009 1.0000
15.500 1.1298 0.07613 0.07174 0.0070 0.0009 1.0000
15.750 1.1232 0.08070 0.07645 0.0056 0.0009 1.0000
16.000 1.1131 0.08596 0.08185 0.0038 0.0009 1.0000
16.250 1.1084 0.09049 0.08650 0.0021 0.0009 1.0000
16.500 1.0944 0.09679 0.09296 -0.0004 0.0009 1.0000
16.750 1.0827 0.10280 0.09911 -0.0029 0.0009 1.0000
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Polar data table (+)
Polar graphs
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