MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.9 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh104-il-1000000-n5.txt Download as CSV file: xf-mh104-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9670 0.08448 0.08137 -0.0175 1.0000 0.0030
-16.250 -0.9828 0.07797 0.07475 -0.0211 1.0000 0.0030
-16.000 -1.0008 0.07137 0.06804 -0.0247 1.0000 0.0030
-15.750 -1.0232 0.06433 0.06087 -0.0285 1.0000 0.0030
-15.500 -1.0363 0.05878 0.05519 -0.0315 1.0000 0.0030
-15.250 -1.0496 0.05332 0.04962 -0.0345 1.0000 0.0030
-15.000 -1.0561 0.04894 0.04514 -0.0368 1.0000 0.0030
-14.750 -1.0666 0.04420 0.04027 -0.0392 1.0000 0.0030
-14.500 -1.0757 0.03996 0.03589 -0.0410 1.0000 0.0030
-14.250 -1.0759 0.03707 0.03291 -0.0419 1.0000 0.0030
-14.000 -1.0792 0.03416 0.02989 -0.0424 1.0000 0.0030
-13.750 -1.0806 0.03176 0.02739 -0.0422 1.0000 0.0030
-13.500 -1.0874 0.02923 0.02473 -0.0412 1.0000 0.0030
-13.250 -1.0807 0.02794 0.02338 -0.0401 1.0000 0.0030
-13.000 -1.0775 0.02654 0.02190 -0.0385 1.0000 0.0030
-12.750 -1.0743 0.02526 0.02053 -0.0364 1.0000 0.0030
-12.500 -1.0693 0.02416 0.01936 -0.0341 1.0000 0.0030
-12.250 -1.0672 0.02299 0.01810 -0.0311 1.0000 0.0031
-12.000 -1.0641 0.02194 0.01696 -0.0279 1.0000 0.0031
-11.750 -1.0416 0.02101 0.01582 -0.0281 0.8982 0.0031
-11.500 -1.0365 0.02051 0.01505 -0.0244 0.8390 0.0032
-11.250 -1.0254 0.01979 0.01415 -0.0219 0.8076 0.0032
-11.000 -1.0115 0.01911 0.01332 -0.0199 0.7831 0.0033
-10.750 -0.9951 0.01848 0.01257 -0.0182 0.7618 0.0034
-10.500 -0.9764 0.01798 0.01195 -0.0168 0.7428 0.0034
-10.250 -0.9572 0.01745 0.01132 -0.0155 0.7262 0.0035
-10.000 -0.9366 0.01699 0.01077 -0.0144 0.7107 0.0036
-9.750 -0.9158 0.01651 0.01020 -0.0133 0.6964 0.0037
-9.500 -0.8938 0.01610 0.00970 -0.0124 0.6825 0.0038
-9.250 -0.8719 0.01566 0.00917 -0.0114 0.6697 0.0039
-9.000 -0.8492 0.01526 0.00870 -0.0106 0.6579 0.0041
-8.750 -0.8262 0.01486 0.00821 -0.0097 0.6461 0.0042
-8.500 -0.8028 0.01448 0.00775 -0.0090 0.6346 0.0043
-8.250 -0.7790 0.01413 0.00732 -0.0083 0.6229 0.0045
-7.750 -0.7304 0.01346 0.00651 -0.0070 0.6023 0.0048
-7.500 -0.7060 0.01311 0.00610 -0.0063 0.5931 0.0052
-7.250 -0.6810 0.01281 0.00575 -0.0058 0.5834 0.0056
-7.000 -0.6556 0.01255 0.00543 -0.0053 0.5740 0.0061
-6.750 -0.6300 0.01231 0.00513 -0.0048 0.5641 0.0068
-6.500 -0.6045 0.01203 0.00482 -0.0044 0.5547 0.0080
-6.250 -0.5786 0.01180 0.00454 -0.0040 0.5464 0.0094
-6.000 -0.5526 0.01157 0.00428 -0.0036 0.5381 0.0118
-5.750 -0.5266 0.01133 0.00403 -0.0032 0.5306 0.0155
-5.500 -0.5004 0.01110 0.00380 -0.0028 0.5225 0.0202
-5.250 -0.4743 0.01088 0.00356 -0.0024 0.5149 0.0262
-5.000 -0.4482 0.01064 0.00333 -0.0021 0.5067 0.0359
-4.750 -0.4230 0.01031 0.00307 -0.0016 0.4995 0.0561
-4.500 -0.3989 0.00984 0.00278 -0.0010 0.4925 0.0957
-4.250 -0.3751 0.00937 0.00251 -0.0003 0.4863 0.1465
-4.000 -0.3498 0.00903 0.00232 0.0002 0.4803 0.1866
-3.750 -0.3235 0.00883 0.00219 0.0005 0.4738 0.2117
-3.500 -0.2965 0.00869 0.00208 0.0007 0.4681 0.2318
-3.250 -0.2699 0.00850 0.00197 0.0010 0.4616 0.2595
-3.000 -0.2430 0.00837 0.00188 0.0012 0.4557 0.2810
-2.750 -0.2153 0.00828 0.00181 0.0013 0.4503 0.2946
-2.500 -0.1876 0.00821 0.00174 0.0014 0.4450 0.3069
-2.250 -0.1600 0.00815 0.00168 0.0016 0.4401 0.3196
-2.000 -0.1321 0.00808 0.00162 0.0016 0.4359 0.3319
-1.750 -0.1043 0.00802 0.00158 0.0017 0.4311 0.3445
-1.500 -0.0765 0.00799 0.00154 0.0018 0.4262 0.3569
-1.000 -0.0207 0.00788 0.00147 0.0020 0.4178 0.3842
-0.750 0.0071 0.00784 0.00145 0.0020 0.4137 0.3983
-0.500 0.0348 0.00781 0.00143 0.0021 0.4099 0.4134
-0.250 0.0628 0.00776 0.00142 0.0022 0.4068 0.4278
0.000 0.0906 0.00772 0.00141 0.0023 0.4030 0.4447
0.250 0.1183 0.00768 0.00141 0.0023 0.3991 0.4616
0.500 0.1459 0.00766 0.00142 0.0024 0.3955 0.4785
0.750 0.1736 0.00761 0.00142 0.0025 0.3926 0.4983
1.000 0.2012 0.00756 0.00143 0.0026 0.3892 0.5198
1.250 0.2286 0.00752 0.00145 0.0028 0.3856 0.5423
1.500 0.2557 0.00748 0.00148 0.0030 0.3820 0.5685
1.750 0.2828 0.00744 0.00151 0.0031 0.3787 0.5950
2.250 0.3367 0.00733 0.00159 0.0036 0.3724 0.6544
2.500 0.3632 0.00729 0.00163 0.0039 0.3690 0.6862
2.750 0.3894 0.00726 0.00169 0.0043 0.3654 0.7173
3.000 0.4156 0.00721 0.00175 0.0047 0.3626 0.7498
3.250 0.4417 0.00715 0.00181 0.0051 0.3595 0.7829
3.500 0.4677 0.00712 0.00188 0.0056 0.3562 0.8146
3.750 0.4938 0.00710 0.00197 0.0061 0.3526 0.8464
4.000 0.5205 0.00711 0.00207 0.0064 0.3490 0.8769
4.250 0.5499 0.00712 0.00217 0.0062 0.3459 0.9039
4.500 0.5825 0.00718 0.00229 0.0052 0.3418 0.9254
4.750 0.6179 0.00730 0.00242 0.0036 0.3371 0.9404
5.000 0.6545 0.00742 0.00255 0.0017 0.3326 0.9501
5.250 0.6893 0.00753 0.00266 0.0002 0.3275 0.9573
5.500 0.7237 0.00767 0.00279 -0.0013 0.3217 0.9630
5.750 0.7533 0.00780 0.00292 -0.0017 0.3164 0.9695
6.000 0.7877 0.00794 0.00306 -0.0032 0.3091 0.9727
6.250 0.8196 0.00810 0.00320 -0.0042 0.3029 0.9768
6.500 0.8478 0.00826 0.00336 -0.0043 0.2952 0.9821
6.750 0.8849 0.00846 0.00353 -0.0065 0.2856 0.9844
7.000 0.9206 0.00869 0.00373 -0.0083 0.2745 0.9872
7.250 0.9533 0.00892 0.00393 -0.0096 0.2628 0.9899
7.500 0.9835 0.00920 0.00416 -0.0104 0.2498 0.9923
7.750 1.0144 0.00949 0.00441 -0.0114 0.2365 0.9941
8.000 1.0467 0.00980 0.00468 -0.0127 0.2231 0.9956
8.250 1.0783 0.01015 0.00497 -0.0140 0.2090 0.9973
8.500 1.1093 0.01054 0.00530 -0.0151 0.1942 0.9989
8.750 1.1390 0.01097 0.00567 -0.0161 0.1791 1.0000
9.000 1.1580 0.01138 0.00603 -0.0147 0.1660 1.0000
9.250 1.1761 0.01184 0.00643 -0.0133 0.1520 1.0000
9.500 1.1937 0.01230 0.00684 -0.0118 0.1393 1.0000
9.750 1.2099 0.01283 0.00731 -0.0101 0.1255 1.0000
10.000 1.2251 0.01339 0.00780 -0.0082 0.1122 1.0000
10.250 1.2411 0.01387 0.00826 -0.0065 0.1031 1.0000
10.500 1.2553 0.01442 0.00877 -0.0046 0.0938 1.0000
10.750 1.2688 0.01496 0.00928 -0.0025 0.0858 1.0000
11.000 1.2813 0.01551 0.00982 -0.0003 0.0779 1.0000
11.250 1.2916 0.01612 0.01042 0.0021 0.0712 1.0000
11.500 1.2959 0.01683 0.01111 0.0055 0.0635 1.0000
11.750 1.2968 0.01753 0.01181 0.0093 0.0577 1.0000
12.000 1.2953 0.01863 0.01288 0.0126 0.0500 1.0000
12.250 1.2957 0.01999 0.01424 0.0148 0.0433 1.0000
12.500 1.2969 0.02162 0.01587 0.0162 0.0366 1.0000
12.750 1.3012 0.02326 0.01754 0.0170 0.0330 1.0000
13.000 1.3028 0.02530 0.01959 0.0176 0.0286 1.0000
13.250 1.3063 0.02729 0.02163 0.0179 0.0258 1.0000
13.500 1.3063 0.02973 0.02410 0.0180 0.0226 1.0000
13.750 1.3050 0.03236 0.02677 0.0180 0.0192 1.0000
14.000 1.3061 0.03481 0.02927 0.0179 0.0181 1.0000
14.250 1.3034 0.03768 0.03218 0.0177 0.0155 1.0000
14.500 1.3036 0.04030 0.03486 0.0175 0.0147 1.0000
14.750 1.2989 0.04343 0.03804 0.0171 0.0129 1.0000
15.000 1.2977 0.04625 0.04093 0.0168 0.0124 1.0000
15.250 1.2940 0.04937 0.04411 0.0163 0.0115 1.0000
15.500 1.2906 0.05258 0.04738 0.0158 0.0108 1.0000
15.750 1.2872 0.05586 0.05072 0.0151 0.0098 1.0000
16.000 1.2842 0.05914 0.05406 0.0144 0.0093 1.0000
16.250 1.2784 0.06281 0.05779 0.0135 0.0084 1.0000
16.500 1.2761 0.06610 0.06115 0.0127 0.0080 1.0000
16.750 1.2735 0.06948 0.06460 0.0119 0.0078 1.0000
17.000 1.2692 0.07312 0.06830 0.0109 0.0072 1.0000
17.250 1.2655 0.07673 0.07198 0.0099 0.0068 1.0000
17.500 1.2609 0.08048 0.07578 0.0088 0.0065 1.0000
17.750 1.2557 0.08436 0.07973 0.0076 0.0062 1.0000
18.000 1.2520 0.08808 0.08352 0.0065 0.0059 1.0000
18.250 1.2475 0.09195 0.08746 0.0053 0.0056 1.0000
18.500 1.2421 0.09596 0.09154 0.0040 0.0053 1.0000
18.750 1.2366 0.10004 0.09568 0.0026 0.0049 1.0000
19.000 1.2316 0.10412 0.09983 0.0012 0.0048 1.0000
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Polar data table (+)
Polar graphs
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