MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 50,000 Max Cl/Cd: 33.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh46-il-50000-n5.txt Download as CSV file: xf-mh46-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5597 0.08102 0.07450 -0.0181 1.0000 0.0310
-8.500 -0.5648 0.07594 0.06946 -0.0218 1.0000 0.0307
-8.250 -0.5723 0.07125 0.06476 -0.0242 1.0000 0.0305
-8.000 -0.5766 0.06665 0.06008 -0.0263 1.0000 0.0302
-7.750 -0.5806 0.06177 0.05504 -0.0280 1.0000 0.0301
-7.500 -0.5809 0.05713 0.05017 -0.0291 1.0000 0.0300
-7.250 -0.5779 0.05263 0.04536 -0.0296 1.0000 0.0300
-7.000 -0.5717 0.04827 0.04057 -0.0296 1.0000 0.0302
-6.750 -0.5614 0.04439 0.03616 -0.0291 1.0000 0.0308
-6.500 -0.5495 0.04087 0.03237 -0.0285 1.0000 0.0326
-6.250 -0.5335 0.03834 0.02960 -0.0278 1.0000 0.0349
-6.000 -0.5158 0.03562 0.02649 -0.0268 1.0000 0.0374
-5.750 -0.4959 0.03281 0.02320 -0.0256 1.0000 0.0394
-5.500 -0.4741 0.03031 0.02022 -0.0242 1.0000 0.0418
-5.250 -0.4545 0.02835 0.01821 -0.0231 1.0000 0.0476
-5.000 -0.4329 0.02664 0.01612 -0.0217 1.0000 0.0557
-4.750 -0.4132 0.02506 0.01446 -0.0202 1.0000 0.0676
-4.500 -0.3946 0.02349 0.01299 -0.0187 1.0000 0.0858
-4.250 -0.3755 0.02208 0.01170 -0.0174 1.0000 0.1223
-4.000 -0.3562 0.02070 0.01065 -0.0164 1.0000 0.1835
-3.750 -0.3394 0.01972 0.01002 -0.0149 1.0000 0.2632
-3.500 -0.3238 0.01900 0.00957 -0.0130 1.0000 0.3418
-3.250 -0.3087 0.01840 0.00923 -0.0109 1.0000 0.4173
-3.000 -0.2937 0.01790 0.00889 -0.0086 1.0000 0.4937
-2.750 -0.2785 0.01742 0.00866 -0.0061 1.0000 0.5724
-2.500 -0.2621 0.01698 0.00850 -0.0036 1.0000 0.6616
-2.250 -0.2224 0.01658 0.00841 -0.0046 0.9964 0.8006
-2.000 -0.1303 0.01648 0.00799 -0.0160 0.9999 0.9668
-1.750 -0.0764 0.01657 0.00766 -0.0221 0.9895 1.0000
-1.500 -0.0326 0.01667 0.00743 -0.0261 0.9742 1.0000
-1.250 0.0123 0.01676 0.00722 -0.0302 0.9602 1.0000
-1.000 0.0565 0.01685 0.00708 -0.0339 0.9462 1.0000
-0.750 0.0979 0.01693 0.00698 -0.0370 0.9314 1.0000
-0.500 0.1366 0.01703 0.00691 -0.0393 0.9162 1.0000
-0.250 0.1726 0.01713 0.00688 -0.0410 0.9007 1.0000
0.000 0.2032 0.01726 0.00691 -0.0416 0.8837 1.0000
0.250 0.2316 0.01741 0.00697 -0.0416 0.8665 1.0000
0.500 0.2586 0.01756 0.00704 -0.0412 0.8497 1.0000
0.750 0.2844 0.01771 0.00712 -0.0405 0.8332 1.0000
1.000 0.3090 0.01787 0.00722 -0.0396 0.8169 1.0000
1.250 0.3318 0.01807 0.00737 -0.0383 0.7993 1.0000
1.500 0.3549 0.01825 0.00754 -0.0371 0.7822 1.0000
1.750 0.3780 0.01842 0.00769 -0.0357 0.7655 1.0000
2.000 0.4011 0.01858 0.00782 -0.0343 0.7490 1.0000
2.250 0.4236 0.01878 0.00802 -0.0330 0.7311 1.0000
2.500 0.4462 0.01897 0.00822 -0.0316 0.7129 1.0000
2.750 0.4692 0.01914 0.00845 -0.0302 0.6952 1.0000
3.000 0.4922 0.01931 0.00864 -0.0288 0.6770 1.0000
3.250 0.5151 0.01952 0.00890 -0.0275 0.6571 1.0000
3.500 0.5386 0.01968 0.00908 -0.0261 0.6383 1.0000
3.750 0.5617 0.01991 0.00942 -0.0249 0.6170 1.0000
4.000 0.5851 0.02009 0.00963 -0.0235 0.5968 1.0000
4.250 0.6082 0.02034 0.00996 -0.0222 0.5739 1.0000
4.500 0.6314 0.02058 0.01025 -0.0209 0.5514 1.0000
4.750 0.6545 0.02084 0.01061 -0.0196 0.5279 1.0000
5.000 0.6772 0.02116 0.01101 -0.0183 0.5026 1.0000
5.250 0.6997 0.02152 0.01143 -0.0170 0.4762 1.0000
5.500 0.7219 0.02192 0.01189 -0.0157 0.4488 1.0000
5.750 0.7437 0.02237 0.01239 -0.0144 0.4201 1.0000
6.000 0.7649 0.02288 0.01301 -0.0131 0.3902 1.0000
6.250 0.7854 0.02348 0.01365 -0.0118 0.3583 1.0000
6.500 0.8051 0.02416 0.01437 -0.0104 0.3247 1.0000
6.750 0.8237 0.02495 0.01514 -0.0091 0.2906 1.0000
7.000 0.8412 0.02587 0.01606 -0.0077 0.2547 1.0000
7.250 0.8574 0.02696 0.01710 -0.0064 0.2189 1.0000
7.500 0.8721 0.02825 0.01831 -0.0050 0.1852 1.0000
7.750 0.8859 0.02974 0.01970 -0.0036 0.1549 1.0000
8.000 0.8984 0.03138 0.02129 -0.0022 0.1276 1.0000
8.250 0.9112 0.03321 0.02324 -0.0007 0.1073 1.0000
8.500 0.9218 0.03505 0.02501 0.0007 0.0909 1.0000
8.750 0.9348 0.03708 0.02715 0.0022 0.0792 1.0000
9.000 0.9484 0.03920 0.02948 0.0037 0.0697 1.0000
9.250 0.9588 0.04133 0.03172 0.0051 0.0615 1.0000
9.500 0.9711 0.04369 0.03427 0.0064 0.0559 1.0000
9.750 0.9842 0.04650 0.03717 0.0077 0.0522 1.0000
10.000 0.9905 0.04953 0.04070 0.0091 0.0483 1.0000
10.250 0.9922 0.05212 0.04351 0.0105 0.0447 1.0000
10.500 0.9933 0.05467 0.04607 0.0118 0.0420 1.0000
10.750 0.9886 0.05832 0.04998 0.0130 0.0408 1.0000
11.000 0.9788 0.06223 0.05423 0.0135 0.0403 1.0000
11.250 0.9654 0.06667 0.05896 0.0130 0.0399 1.0000
11.500 0.9500 0.07159 0.06412 0.0115 0.0398 1.0000
11.750 0.9326 0.07722 0.06995 0.0089 0.0399 1.0000
12.000 0.9146 0.08346 0.07635 0.0054 0.0401 1.0000
12.250 0.8946 0.09079 0.08381 0.0009 0.0403 1.0000
12.500 0.8764 0.09850 0.09161 -0.0039 0.0407 1.0000
12.750 0.8595 0.10663 0.09979 -0.0088 0.0411 1.0000
13.000 0.8430 0.11538 0.10855 -0.0138 0.0413 1.0000
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Polar data table (+)
Polar graphs
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