MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.43 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh45-il-1000000.txt Download as CSV file: xf-mh45-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5986 0.08386 0.08247 0.0094 1.0000 0.0085
-8.750 -0.6060 0.07780 0.07644 0.0054 1.0000 0.0085
-8.500 -0.6192 0.07064 0.06932 0.0000 1.0000 0.0084
-8.250 -0.5749 0.05649 0.05497 0.0016 0.8587 0.0090
-8.000 -0.6229 0.04466 0.04296 -0.0080 0.8456 0.0084
-7.750 -0.6390 0.03760 0.03565 -0.0100 0.8358 0.0084
-7.500 -0.6432 0.03169 0.02946 -0.0106 0.8278 0.0085
-7.250 -0.6390 0.02649 0.02396 -0.0107 0.8198 0.0088
-7.000 -0.6289 0.02206 0.01916 -0.0102 0.8129 0.0094
-6.750 -0.6066 0.02103 0.01778 -0.0094 0.8051 0.0101
-6.500 -0.5902 0.01824 0.01464 -0.0088 0.7983 0.0101
-6.000 -0.5705 0.01779 0.01280 -0.0074 0.7984 0.0063
-5.750 -0.5487 0.01432 0.00883 -0.0057 0.7913 0.0049
-5.500 -0.5228 0.01352 0.00789 -0.0052 0.7845 0.0048
-5.250 -0.4969 0.01273 0.00700 -0.0047 0.7772 0.0047
-5.000 -0.4710 0.01198 0.00613 -0.0042 0.7704 0.0047
-4.750 -0.4451 0.01120 0.00524 -0.0037 0.7631 0.0047
-4.500 -0.4189 0.01052 0.00444 -0.0033 0.7564 0.0049
-4.250 -0.3919 0.00999 0.00383 -0.0029 0.7491 0.0052
-4.000 -0.3646 0.00962 0.00339 -0.0027 0.7423 0.0058
-3.750 -0.3368 0.00932 0.00303 -0.0025 0.7348 0.0067
-3.500 -0.3094 0.00897 0.00261 -0.0022 0.7280 0.0092
-3.250 -0.2820 0.00853 0.00224 -0.0019 0.7205 0.0269
-3.000 -0.2552 0.00811 0.00197 -0.0017 0.7136 0.0673
-2.750 -0.2284 0.00762 0.00174 -0.0016 0.7059 0.1322
-2.500 -0.2017 0.00723 0.00158 -0.0014 0.6987 0.1998
-2.250 -0.1746 0.00688 0.00145 -0.0013 0.6906 0.2632
-2.000 -0.1468 0.00672 0.00135 -0.0012 0.6829 0.2972
-1.750 -0.1192 0.00648 0.00125 -0.0011 0.6743 0.3464
-1.500 -0.0917 0.00627 0.00118 -0.0010 0.6659 0.3986
-1.250 -0.0644 0.00607 0.00111 -0.0008 0.6570 0.4520
-1.000 -0.0367 0.00590 0.00106 -0.0007 0.6475 0.4958
-0.750 -0.0091 0.00576 0.00100 -0.0006 0.6380 0.5399
-0.500 0.0183 0.00561 0.00096 -0.0004 0.6277 0.5896
-0.250 0.0454 0.00544 0.00093 -0.0001 0.6167 0.6426
0.000 0.0718 0.00525 0.00091 0.0003 0.6055 0.7051
0.250 0.0973 0.00504 0.00090 0.0010 0.5937 0.7764
0.500 0.1217 0.00481 0.00091 0.0020 0.5812 0.8574
0.750 0.1555 0.00468 0.00094 0.0011 0.5669 0.9405
1.000 0.2073 0.00476 0.00097 -0.0039 0.5492 0.9729
1.250 0.2463 0.00486 0.00099 -0.0063 0.5320 0.9876
1.500 0.2848 0.00498 0.00102 -0.0085 0.5136 0.9961
1.750 0.3231 0.00508 0.00103 -0.0108 0.4945 1.0000
2.000 0.3499 0.00518 0.00106 -0.0105 0.4763 1.0000
2.250 0.3767 0.00530 0.00110 -0.0103 0.4583 1.0000
2.500 0.4036 0.00543 0.00115 -0.0101 0.4406 1.0000
2.750 0.4305 0.00555 0.00120 -0.0099 0.4233 1.0000
3.000 0.4575 0.00568 0.00127 -0.0097 0.4057 1.0000
3.250 0.4844 0.00583 0.00135 -0.0095 0.3884 1.0000
3.500 0.5114 0.00599 0.00144 -0.0093 0.3712 1.0000
3.750 0.5383 0.00615 0.00154 -0.0091 0.3539 1.0000
4.000 0.5653 0.00631 0.00165 -0.0089 0.3371 1.0000
4.250 0.5922 0.00650 0.00177 -0.0088 0.3186 1.0000
4.500 0.6190 0.00669 0.00190 -0.0086 0.3013 1.0000
4.750 0.6457 0.00691 0.00204 -0.0085 0.2820 1.0000
5.000 0.6725 0.00711 0.00220 -0.0083 0.2641 1.0000
5.250 0.6991 0.00736 0.00237 -0.0081 0.2446 1.0000
5.500 0.7255 0.00763 0.00256 -0.0080 0.2247 1.0000
5.750 0.7520 0.00788 0.00276 -0.0078 0.2069 1.0000
6.000 0.7781 0.00819 0.00298 -0.0076 0.1876 1.0000
6.250 0.8042 0.00849 0.00322 -0.0074 0.1698 1.0000
6.500 0.8303 0.00879 0.00347 -0.0072 0.1539 1.0000
6.750 0.8562 0.00912 0.00373 -0.0070 0.1380 1.0000
7.000 0.8820 0.00945 0.00402 -0.0068 0.1246 1.0000
7.250 0.9076 0.00979 0.00431 -0.0066 0.1116 1.0000
7.500 0.9331 0.01015 0.00463 -0.0064 0.0990 1.0000
7.750 0.9584 0.01051 0.00495 -0.0061 0.0880 1.0000
8.000 0.9835 0.01090 0.00531 -0.0059 0.0782 1.0000
8.250 1.0087 0.01127 0.00566 -0.0056 0.0703 1.0000
8.500 1.0337 0.01163 0.00602 -0.0053 0.0627 1.0000
8.750 1.0580 0.01209 0.00645 -0.0050 0.0545 1.0000
9.000 1.0828 0.01246 0.00683 -0.0047 0.0494 1.0000
9.250 1.1068 0.01293 0.00729 -0.0043 0.0430 1.0000
9.500 1.1304 0.01341 0.00776 -0.0040 0.0371 1.0000
9.750 1.1539 0.01389 0.00825 -0.0036 0.0319 1.0000
10.000 1.1759 0.01454 0.00886 -0.0030 0.0254 1.0000
10.250 1.1987 0.01504 0.00937 -0.0026 0.0217 1.0000
10.500 1.2201 0.01569 0.01003 -0.0020 0.0180 1.0000
10.750 1.2417 0.01627 0.01063 -0.0014 0.0159 1.0000
11.000 1.2608 0.01710 0.01150 -0.0006 0.0132 1.0000
11.250 1.2822 0.01761 0.01207 0.0000 0.0124 1.0000
11.500 1.3019 0.01825 0.01275 0.0007 0.0111 1.0000
11.750 1.3186 0.01914 0.01368 0.0017 0.0096 1.0000
12.000 1.3366 0.01982 0.01442 0.0026 0.0088 1.0000
12.250 1.3537 0.02051 0.01516 0.0035 0.0079 1.0000
12.500 1.3671 0.02142 0.01610 0.0048 0.0069 1.0000
12.750 1.3760 0.02240 0.01716 0.0067 0.0061 1.0000
13.000 1.3842 0.02326 0.01811 0.0085 0.0055 1.0000
13.250 1.3863 0.02478 0.01967 0.0102 0.0041 1.0000
13.500 1.3937 0.02612 0.02109 0.0112 0.0037 1.0000
13.750 1.3995 0.02772 0.02278 0.0119 0.0034 1.0000
14.000 1.4042 0.02952 0.02466 0.0123 0.0030 1.0000
14.250 1.3978 0.03260 0.02786 0.0126 0.0024 1.0000
14.500 1.3985 0.03510 0.03047 0.0125 0.0021 1.0000
14.750 1.3996 0.03768 0.03316 0.0121 0.0023 1.0000
15.000 1.3983 0.04065 0.03624 0.0115 0.0021 1.0000
15.250 1.3940 0.04410 0.03981 0.0105 0.0019 1.0000
15.500 1.3827 0.04865 0.04449 0.0089 0.0018 1.0000
15.750 1.3812 0.05205 0.04800 0.0076 0.0019 1.0000
16.000 1.3672 0.05733 0.05342 0.0054 0.0019 1.0000
16.250 1.3525 0.06291 0.05913 0.0029 0.0017 1.0000
16.500 1.3425 0.06805 0.06438 0.0005 0.0018 1.0000
16.750 1.3206 0.07529 0.07177 -0.0030 0.0018 1.0000
17.000 1.2978 0.08287 0.07948 -0.0067 0.0017 1.0000
17.250 1.2834 0.08923 0.08597 -0.0098 0.0018 1.0000
17.500 1.2577 0.09780 0.09467 -0.0141 0.0018 1.0000
17.750 1.2288 0.10725 0.10427 -0.0189 0.0018 1.0000
18.000 1.2115 0.11468 0.11181 -0.0227 0.0019 1.0000
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Polar data table (+)
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