MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 500,000 Max Cl/Cd: 81.33 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh46-il-500000.txt Download as CSV file: xf-mh46-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5528 0.08223 0.08016 -0.0069 1.0000 0.0163
-8.500 -0.5572 0.07732 0.07529 -0.0101 1.0000 0.0164
-8.250 -0.5667 0.07173 0.06974 -0.0145 1.0000 0.0165
-8.000 -0.5809 0.06445 0.06245 -0.0212 1.0000 0.0162
-7.750 -0.5874 0.05731 0.05519 -0.0256 1.0000 0.0163
-7.500 -0.5884 0.05164 0.04935 -0.0276 1.0000 0.0166
-7.250 -0.5848 0.04667 0.04418 -0.0284 1.0000 0.0172
-7.000 -0.5776 0.04209 0.03934 -0.0286 1.0000 0.0180
-6.750 -0.5658 0.03819 0.03514 -0.0281 1.0000 0.0192
-6.500 -0.5410 0.03814 0.03477 -0.0270 1.0000 0.0211
-6.250 -0.5263 0.03538 0.03169 -0.0261 1.0000 0.0213
-5.750 -0.5064 0.01847 0.01317 -0.0213 0.9915 0.0085
-5.500 -0.4696 0.01752 0.01208 -0.0231 0.9815 0.0082
-5.250 -0.4375 0.01525 0.00957 -0.0240 0.9693 0.0078
-5.000 -0.4092 0.01372 0.00783 -0.0239 0.9541 0.0078
-4.750 -0.3860 0.01272 0.00667 -0.0227 0.9370 0.0078
-4.500 -0.3641 0.01199 0.00579 -0.0212 0.9209 0.0080
-4.250 -0.3430 0.01106 0.00469 -0.0195 0.9062 0.0086
-4.000 -0.3198 0.01044 0.00393 -0.0182 0.8928 0.0110
-3.750 -0.2971 0.00960 0.00319 -0.0168 0.8802 0.0488
-3.500 -0.2734 0.00910 0.00289 -0.0160 0.8683 0.1025
-3.250 -0.2503 0.00850 0.00264 -0.0152 0.8568 0.1930
-3.000 -0.2258 0.00813 0.00245 -0.0146 0.8454 0.2568
-2.750 -0.2003 0.00785 0.00229 -0.0140 0.8339 0.3064
-2.500 -0.1747 0.00760 0.00214 -0.0135 0.8228 0.3564
-2.250 -0.1497 0.00731 0.00202 -0.0129 0.8120 0.4218
-2.000 -0.1250 0.00703 0.00191 -0.0122 0.8016 0.4902
-1.750 -0.0998 0.00681 0.00181 -0.0115 0.7908 0.5463
-1.500 -0.0751 0.00656 0.00174 -0.0108 0.7799 0.6096
-1.250 -0.0512 0.00629 0.00167 -0.0097 0.7692 0.6804
-1.000 -0.0285 0.00598 0.00161 -0.0083 0.7588 0.7648
-0.750 -0.0022 0.00567 0.00160 -0.0075 0.7484 0.8674
-0.500 0.0584 0.00563 0.00162 -0.0142 0.7365 0.9428
-0.250 0.1075 0.00571 0.00162 -0.0186 0.7243 0.9676
0.000 0.1476 0.00581 0.00164 -0.0210 0.7116 0.9843
0.250 0.1911 0.00589 0.00163 -0.0244 0.6979 0.9950
0.500 0.2304 0.00592 0.00157 -0.0269 0.6834 1.0000
0.750 0.2554 0.00595 0.00153 -0.0262 0.6691 1.0000
1.000 0.2807 0.00599 0.00149 -0.0257 0.6542 1.0000
1.250 0.3060 0.00605 0.00147 -0.0251 0.6388 1.0000
1.500 0.3315 0.00611 0.00147 -0.0246 0.6222 1.0000
1.750 0.3571 0.00618 0.00148 -0.0241 0.6052 1.0000
2.000 0.3827 0.00627 0.00150 -0.0236 0.5872 1.0000
2.500 0.4340 0.00648 0.00159 -0.0226 0.5492 1.0000
2.750 0.4597 0.00662 0.00165 -0.0221 0.5290 1.0000
3.000 0.4854 0.00676 0.00173 -0.0217 0.5086 1.0000
3.250 0.5110 0.00692 0.00182 -0.0212 0.4878 1.0000
3.500 0.5367 0.00708 0.00194 -0.0208 0.4667 1.0000
3.750 0.5623 0.00727 0.00206 -0.0203 0.4447 1.0000
4.000 0.5879 0.00746 0.00220 -0.0199 0.4222 1.0000
4.250 0.6134 0.00768 0.00235 -0.0195 0.3989 1.0000
4.500 0.6387 0.00792 0.00254 -0.0191 0.3747 1.0000
4.750 0.6639 0.00818 0.00272 -0.0186 0.3483 1.0000
5.000 0.6889 0.00847 0.00293 -0.0182 0.3203 1.0000
5.250 0.7137 0.00879 0.00316 -0.0177 0.2906 1.0000
5.500 0.7383 0.00914 0.00342 -0.0172 0.2598 1.0000
5.750 0.7625 0.00954 0.00371 -0.0167 0.2284 1.0000
6.000 0.7863 0.01000 0.00406 -0.0162 0.1966 1.0000
6.250 0.8101 0.01047 0.00441 -0.0156 0.1652 1.0000
6.500 0.8335 0.01096 0.00480 -0.0150 0.1369 1.0000
6.750 0.8565 0.01151 0.00523 -0.0144 0.1086 1.0000
7.000 0.8789 0.01212 0.00572 -0.0137 0.0812 1.0000
7.250 0.9009 0.01279 0.00628 -0.0130 0.0579 1.0000
7.500 0.9221 0.01357 0.00699 -0.0120 0.0404 1.0000
7.750 0.9426 0.01444 0.00788 -0.0110 0.0299 1.0000
8.000 0.9647 0.01502 0.00851 -0.0102 0.0251 1.0000
8.250 0.9824 0.01619 0.00977 -0.0087 0.0206 1.0000
8.500 1.0063 0.01646 0.01007 -0.0082 0.0176 1.0000
8.750 1.0248 0.01740 0.01105 -0.0071 0.0143 1.0000
9.000 1.0436 0.01827 0.01203 -0.0059 0.0123 1.0000
9.250 1.0636 0.01897 0.01279 -0.0049 0.0102 1.0000
9.500 1.0708 0.02107 0.01504 -0.0024 0.0079 1.0000
9.750 1.0887 0.02191 0.01599 -0.0011 0.0069 1.0000
10.000 1.1032 0.02303 0.01726 0.0005 0.0060 1.0000
10.250 1.1144 0.02442 0.01879 0.0024 0.0058 1.0000
10.500 1.1239 0.02584 0.02032 0.0044 0.0054 1.0000
10.750 1.1288 0.02752 0.02215 0.0069 0.0053 1.0000
11.000 1.1272 0.02940 0.02417 0.0100 0.0051 1.0000
11.250 1.1257 0.03152 0.02647 0.0125 0.0050 1.0000
11.500 1.1239 0.03388 0.02901 0.0143 0.0050 1.0000
11.750 1.1182 0.03685 0.03219 0.0156 0.0049 1.0000
12.000 1.1114 0.04014 0.03569 0.0164 0.0049 1.0000
12.250 1.1055 0.04350 0.03925 0.0165 0.0049 1.0000
12.500 1.0973 0.04734 0.04328 0.0159 0.0049 1.0000
12.750 1.0887 0.05144 0.04756 0.0147 0.0049 1.0000
13.000 1.0719 0.05707 0.05341 0.0126 0.0049 1.0000
13.250 1.0640 0.06166 0.05815 0.0103 0.0049 1.0000
13.500 1.0501 0.06755 0.06423 0.0071 0.0050 1.0000
13.750 1.0398 0.07315 0.06997 0.0038 0.0050 1.0000
14.000 1.0230 0.08027 0.07726 -0.0003 0.0051 1.0000
14.250 1.0038 0.08834 0.08549 -0.0051 0.0051 1.0000
14.500 0.9827 0.09747 0.09480 -0.0105 0.0053 1.0000
14.750 0.9582 0.10790 0.10540 -0.0165 0.0054 1.0000
15.000 0.9264 0.12086 0.11852 -0.0236 0.0055 1.0000
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Polar data table (+)
Polar graphs
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