MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 100,000 Max Cl/Cd: 57.86 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh121-il-100000-n5.txt Download as CSV file: xf-mh121-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4302 0.10789 0.10304 -0.0421 1.0000 0.0386
-9.000 -0.4360 0.10497 0.10020 -0.0427 1.0000 0.0388
-8.750 -0.4403 0.10192 0.09723 -0.0424 1.0000 0.0388
-8.250 -0.3782 0.08886 0.08461 -0.0335 1.0000 0.0338
-7.750 -0.3988 0.08128 0.07712 -0.0327 1.0000 0.0243
-7.500 -0.4011 0.07682 0.07271 -0.0341 0.9979 0.0232
-7.250 -0.4868 0.08417 0.07986 -0.0318 1.0000 0.0244
-7.000 -0.4886 0.07997 0.07571 -0.0346 0.9982 0.0239
-6.750 -0.4738 0.07297 0.06868 -0.0442 0.9929 0.0229
-6.500 -0.4598 0.06594 0.06153 -0.0528 0.9870 0.0216
-6.250 -0.4412 0.05889 0.05425 -0.0609 0.9822 0.0201
-6.000 -0.4245 0.05233 0.04736 -0.0663 0.9770 0.0186
-5.750 -0.4003 0.04552 0.03997 -0.0711 0.9728 0.0169
-5.500 -0.3701 0.04064 0.03448 -0.0744 0.9701 0.0159
-5.250 -0.3436 0.03713 0.03046 -0.0760 0.9670 0.0155
-5.000 -0.3174 0.03403 0.02686 -0.0771 0.9638 0.0154
-4.750 -0.2881 0.03107 0.02339 -0.0783 0.9614 0.0153
-4.500 -0.2572 0.02821 0.01989 -0.0795 0.9595 0.0154
-4.250 -0.2259 0.02577 0.01706 -0.0805 0.9580 0.0157
-4.000 -0.1946 0.02379 0.01482 -0.0814 0.9567 0.0162
-3.750 -0.1694 0.02234 0.01323 -0.0811 0.9539 0.0172
-3.500 -0.1418 0.02123 0.01198 -0.0813 0.9511 0.0191
-3.250 -0.1117 0.02048 0.01107 -0.0821 0.9485 0.0275
-3.000 -0.0788 0.01925 0.00977 -0.0834 0.9467 0.0537
-2.750 -0.0487 0.01701 0.00944 -0.0857 0.9458 0.4637
-2.500 -0.0183 0.01699 0.00944 -0.0861 0.9436 0.5478
-2.250 0.0030 0.01705 0.00949 -0.0847 0.9392 0.5989
-2.000 0.0284 0.01711 0.00947 -0.0840 0.9359 0.6437
-1.750 0.0579 0.01714 0.00939 -0.0844 0.9332 0.6674
-1.500 0.0898 0.01715 0.00927 -0.0853 0.9311 0.6834
-1.250 0.1121 0.01720 0.00924 -0.0844 0.9265 0.6982
-1.000 0.1401 0.01724 0.00920 -0.0846 0.9230 0.7143
-0.750 0.1704 0.01727 0.00917 -0.0853 0.9203 0.7312
-0.500 0.2025 0.01728 0.00909 -0.0863 0.9181 0.7494
0.000 0.2503 0.01738 0.00922 -0.0850 0.9089 0.7922
0.250 0.2802 0.01736 0.00926 -0.0854 0.9062 0.8200
0.500 0.3019 0.01737 0.00936 -0.0842 0.9012 0.8570
0.750 0.3314 0.01728 0.00941 -0.0846 0.8969 0.9308
1.000 0.3681 0.01731 0.00940 -0.0868 0.8936 1.0000
1.250 0.3980 0.01749 0.00955 -0.0877 0.8890 1.0000
1.500 0.4269 0.01766 0.00972 -0.0883 0.8836 1.0000
1.750 0.4628 0.01773 0.00982 -0.0901 0.8802 1.0000
2.000 0.4893 0.01792 0.01010 -0.0901 0.8738 1.0000
2.250 0.5225 0.01798 0.01022 -0.0913 0.8688 1.0000
2.500 0.5627 0.01787 0.01021 -0.0937 0.8656 1.0000
2.750 0.5862 0.01802 0.01046 -0.0929 0.8562 1.0000
3.000 0.6222 0.01787 0.01045 -0.0943 0.8500 1.0000
3.250 0.6585 0.01762 0.01048 -0.0955 0.8414 1.0000
3.500 0.6947 0.01719 0.01025 -0.0963 0.8291 1.0000
3.750 0.7326 0.01639 0.00966 -0.0967 0.8095 1.0000
4.000 0.7627 0.01569 0.00914 -0.0957 0.7809 1.0000
4.250 0.7870 0.01524 0.00885 -0.0937 0.7413 1.0000
4.500 0.8338 0.01441 0.00758 -0.0946 0.5753 1.0000
4.750 0.8419 0.01620 0.00802 -0.0905 0.3466 1.0000
5.000 0.8483 0.01828 0.00917 -0.0873 0.1659 1.0000
5.250 0.8621 0.02000 0.01036 -0.0851 0.0801 1.0000
5.500 0.8754 0.02189 0.01178 -0.0828 0.0268 1.0000
5.750 0.8917 0.02350 0.01349 -0.0806 0.0165 1.0000
6.000 0.9090 0.02502 0.01517 -0.0787 0.0124 1.0000
6.250 0.9291 0.02631 0.01662 -0.0774 0.0091 1.0000
6.500 0.9495 0.02806 0.01855 -0.0761 0.0078 1.0000
6.750 0.9724 0.03026 0.02097 -0.0752 0.0073 1.0000
7.000 0.9969 0.03299 0.02401 -0.0745 0.0069 1.0000
7.250 1.0199 0.03614 0.02756 -0.0735 0.0067 1.0000
7.500 1.0385 0.03946 0.03134 -0.0719 0.0066 1.0000
7.750 1.0525 0.04291 0.03526 -0.0697 0.0066 1.0000
8.000 1.0621 0.04643 0.03924 -0.0671 0.0066 1.0000
8.250 1.0674 0.05006 0.04332 -0.0642 0.0066 1.0000
8.500 1.0688 0.05375 0.04742 -0.0610 0.0067 1.0000
8.750 1.0661 0.05749 0.05154 -0.0576 0.0068 1.0000
9.000 1.0584 0.06115 0.05553 -0.0539 0.0069 1.0000
9.250 1.0463 0.06481 0.05947 -0.0502 0.0070 1.0000
9.500 1.0314 0.06869 0.06359 -0.0471 0.0071 1.0000
9.750 1.0148 0.07292 0.06805 -0.0449 0.0072 1.0000
10.000 0.9966 0.07760 0.07293 -0.0439 0.0073 1.0000
10.250 0.9776 0.08289 0.07839 -0.0443 0.0074 1.0000
10.500 0.9587 0.08898 0.08463 -0.0462 0.0075 1.0000
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Polar data table (+)
Polar graphs
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