MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.31 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh46-il-1000000-n5.txt Download as CSV file: xf-mh46-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.7099 0.03790 0.03585 -0.0265 1.0000 0.0023
-8.250 -0.7175 0.03112 0.02856 -0.0255 1.0000 0.0023
-8.000 -0.7110 0.02669 0.02369 -0.0242 0.9924 0.0022
-7.750 -0.6920 0.02258 0.01904 -0.0245 0.9498 0.0022
-7.500 -0.6772 0.02027 0.01633 -0.0226 0.9225 0.0021
-7.250 -0.6600 0.01843 0.01414 -0.0209 0.9022 0.0021
-7.000 -0.6404 0.01685 0.01225 -0.0195 0.8856 0.0021
-6.750 -0.6188 0.01563 0.01078 -0.0184 0.8704 0.0021
-6.500 -0.5964 0.01448 0.00938 -0.0173 0.8562 0.0021
-6.250 -0.5731 0.01357 0.00827 -0.0165 0.8428 0.0021
-6.000 -0.5492 0.01275 0.00728 -0.0157 0.8300 0.0021
-5.500 -0.4998 0.01144 0.00568 -0.0143 0.8060 0.0021
-5.250 -0.4744 0.01091 0.00502 -0.0138 0.7949 0.0021
-5.000 -0.4485 0.01047 0.00447 -0.0133 0.7844 0.0022
-4.750 -0.4224 0.01008 0.00395 -0.0128 0.7740 0.0022
-4.500 -0.3960 0.00973 0.00350 -0.0124 0.7637 0.0023
-4.250 -0.3693 0.00944 0.00313 -0.0121 0.7535 0.0024
-4.000 -0.3424 0.00920 0.00281 -0.0118 0.7436 0.0025
-3.750 -0.3154 0.00895 0.00247 -0.0115 0.7334 0.0031
-3.500 -0.2883 0.00875 0.00222 -0.0112 0.7230 0.0044
-3.250 -0.2615 0.00850 0.00197 -0.0110 0.7129 0.0131
-3.000 -0.2347 0.00826 0.00177 -0.0107 0.7027 0.0282
-2.750 -0.2081 0.00798 0.00158 -0.0105 0.6924 0.0575
-2.500 -0.1823 0.00759 0.00139 -0.0102 0.6816 0.1150
-2.000 -0.1288 0.00714 0.00114 -0.0097 0.6601 0.1934
-1.750 -0.1018 0.00698 0.00105 -0.0096 0.6488 0.2295
-1.500 -0.0752 0.00678 0.00097 -0.0093 0.6367 0.2762
-1.250 -0.0480 0.00667 0.00090 -0.0092 0.6241 0.3071
-1.000 -0.0210 0.00654 0.00084 -0.0090 0.6109 0.3452
-0.750 0.0061 0.00644 0.00079 -0.0088 0.5971 0.3813
-0.500 0.0331 0.00635 0.00076 -0.0086 0.5828 0.4182
-0.250 0.0600 0.00626 0.00073 -0.0084 0.5675 0.4561
0.000 0.0869 0.00619 0.00071 -0.0082 0.5514 0.4945
0.250 0.1137 0.00612 0.00071 -0.0080 0.5346 0.5337
0.500 0.1402 0.00605 0.00071 -0.0077 0.5177 0.5761
0.750 0.1664 0.00598 0.00072 -0.0074 0.5006 0.6228
1.000 0.1920 0.00588 0.00074 -0.0069 0.4834 0.6779
1.250 0.2167 0.00575 0.00077 -0.0062 0.4673 0.7429
1.500 0.2401 0.00558 0.00081 -0.0051 0.4516 0.8197
1.750 0.2683 0.00541 0.00088 -0.0050 0.4337 0.9118
2.000 0.3336 0.00554 0.00098 -0.0134 0.4085 0.9596
2.250 0.3738 0.00571 0.00107 -0.0162 0.3873 0.9753
2.500 0.4044 0.00586 0.00115 -0.0168 0.3685 0.9861
2.750 0.4361 0.00603 0.00125 -0.0177 0.3488 0.9927
3.000 0.4704 0.00620 0.00134 -0.0192 0.3278 0.9964
3.250 0.5058 0.00639 0.00144 -0.0210 0.3060 0.9992
3.500 0.5356 0.00657 0.00155 -0.0215 0.2831 1.0000
3.750 0.5612 0.00678 0.00167 -0.0211 0.2622 1.0000
4.000 0.5868 0.00698 0.00181 -0.0207 0.2415 1.0000
4.250 0.6121 0.00723 0.00196 -0.0203 0.2184 1.0000
4.500 0.6374 0.00750 0.00214 -0.0199 0.1954 1.0000
4.750 0.6625 0.00778 0.00234 -0.0195 0.1716 1.0000
5.000 0.6876 0.00806 0.00254 -0.0190 0.1506 1.0000
5.250 0.7127 0.00836 0.00276 -0.0186 0.1311 1.0000
5.500 0.7373 0.00871 0.00301 -0.0181 0.1078 1.0000
5.750 0.7619 0.00907 0.00327 -0.0177 0.0878 1.0000
6.000 0.7864 0.00943 0.00357 -0.0172 0.0704 1.0000
6.250 0.8106 0.00983 0.00389 -0.0166 0.0540 1.0000
6.500 0.8350 0.01018 0.00420 -0.0161 0.0427 1.0000
6.750 0.8594 0.01053 0.00452 -0.0156 0.0341 1.0000
7.000 0.8837 0.01087 0.00485 -0.0151 0.0273 1.0000
7.250 0.9076 0.01128 0.00523 -0.0145 0.0202 1.0000
7.500 0.9311 0.01171 0.00565 -0.0139 0.0148 1.0000
7.750 0.9551 0.01207 0.00603 -0.0133 0.0119 1.0000
8.000 0.9785 0.01248 0.00644 -0.0127 0.0097 1.0000
8.250 1.0019 0.01289 0.00688 -0.0121 0.0079 1.0000
8.500 1.0255 0.01326 0.00728 -0.0115 0.0070 1.0000
8.750 1.0485 0.01370 0.00774 -0.0109 0.0059 1.0000
9.000 1.0708 0.01420 0.00827 -0.0101 0.0046 1.0000
9.250 1.0934 0.01465 0.00876 -0.0094 0.0039 1.0000
9.500 1.1148 0.01521 0.00936 -0.0086 0.0027 1.0000
9.750 1.1359 0.01579 0.01000 -0.0078 0.0021 1.0000
10.000 1.1561 0.01646 0.01072 -0.0068 0.0016 1.0000
10.250 1.1764 0.01707 0.01141 -0.0059 0.0015 1.0000
10.500 1.1946 0.01791 0.01234 -0.0047 0.0013 1.0000
10.750 1.2119 0.01878 0.01331 -0.0034 0.0012 1.0000
11.000 1.2298 0.01953 0.01415 -0.0022 0.0011 1.0000
11.250 1.2476 0.02022 0.01492 -0.0011 0.0011 1.0000
11.500 1.2640 0.02100 0.01578 0.0002 0.0010 1.0000
11.750 1.2780 0.02194 0.01684 0.0017 0.0010 1.0000
12.000 1.2912 0.02285 0.01786 0.0033 0.0009 1.0000
12.250 1.3016 0.02382 0.01892 0.0052 0.0009 1.0000
12.500 1.3072 0.02483 0.02003 0.0078 0.0009 1.0000
12.750 1.3110 0.02613 0.02145 0.0099 0.0009 1.0000
13.000 1.3130 0.02779 0.02324 0.0116 0.0008 1.0000
13.250 1.3169 0.02948 0.02505 0.0127 0.0008 1.0000
13.500 1.3182 0.03159 0.02728 0.0134 0.0008 1.0000
13.750 1.3235 0.03346 0.02925 0.0137 0.0008 1.0000
14.000 1.3213 0.03628 0.03222 0.0136 0.0008 1.0000
14.250 1.3168 0.03961 0.03570 0.0130 0.0008 1.0000
14.500 1.3143 0.04287 0.03908 0.0120 0.0008 1.0000
14.750 1.3055 0.04719 0.04355 0.0104 0.0008 1.0000
15.000 1.2962 0.05183 0.04833 0.0084 0.0007 1.0000
15.250 1.2845 0.05710 0.05374 0.0059 0.0007 1.0000
15.500 1.2662 0.06365 0.06046 0.0026 0.0007 1.0000
15.750 1.2465 0.07066 0.06762 -0.0010 0.0007 1.0000
16.000 1.2303 0.07734 0.07442 -0.0044 0.0008 1.0000
16.250 1.2044 0.08604 0.08327 -0.0089 0.0008 1.0000
16.500 1.1904 0.09268 0.09000 -0.0121 0.0008 1.0000
16.750 1.1535 0.10393 0.10141 -0.0177 0.0008 1.0000
17.000 1.1266 0.11352 0.11111 -0.0223 0.0008 1.0000
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Polar data table (+)
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