MH 23 8% (mh23-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 50,000 Max Cl/Cd: 33.16 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh23-il-50000-n5.txt Download as CSV file: xf-mh23-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4917 0.09597 0.08895 -0.0268 1.0000 0.0352
-8.750 -0.4955 0.09152 0.08458 -0.0293 1.0000 0.0337
-8.500 -0.5024 0.08670 0.07986 -0.0329 1.0000 0.0324
-8.000 -0.5198 0.07842 0.07173 -0.0365 1.0000 0.0300
-7.750 -0.5241 0.07502 0.06834 -0.0358 1.0000 0.0296
-7.500 -0.5284 0.07172 0.06503 -0.0348 1.0000 0.0292
-7.250 -0.5332 0.06830 0.06143 -0.0336 1.0000 0.0288
-7.000 -0.5365 0.06503 0.05809 -0.0322 1.0000 0.0284
-6.750 -0.5387 0.06169 0.05463 -0.0306 1.0000 0.0280
-6.500 -0.5396 0.05826 0.05104 -0.0287 1.0000 0.0276
-6.250 -0.5382 0.05494 0.04753 -0.0267 1.0000 0.0273
-6.000 -0.5348 0.05162 0.04395 -0.0246 1.0000 0.0269
-5.750 -0.5292 0.04837 0.04039 -0.0223 1.0000 0.0269
-5.500 -0.5211 0.04524 0.03689 -0.0200 1.0000 0.0270
-5.250 -0.5106 0.04230 0.03356 -0.0177 1.0000 0.0274
-5.000 -0.4977 0.03949 0.03028 -0.0155 1.0000 0.0281
-4.750 -0.4822 0.03694 0.02721 -0.0133 1.0000 0.0293
-4.500 -0.4643 0.03471 0.02443 -0.0111 1.0000 0.0303
-4.250 -0.4458 0.03208 0.02145 -0.0094 1.0000 0.0313
-4.000 -0.4253 0.02985 0.01894 -0.0079 1.0000 0.0324
-3.750 -0.4029 0.02789 0.01672 -0.0065 1.0000 0.0342
-3.500 -0.3797 0.02628 0.01487 -0.0050 1.0000 0.0361
-3.250 -0.3557 0.02485 0.01314 -0.0036 1.0000 0.0403
-3.000 -0.3322 0.02363 0.01177 -0.0026 1.0000 0.0531
-2.750 -0.3080 0.02224 0.01033 -0.0017 1.0000 0.0741
-2.500 -0.1421 0.01814 0.00911 -0.0250 1.0000 1.0000
-2.250 -0.1302 0.01803 0.00868 -0.0225 1.0000 1.0000
-2.000 -0.1175 0.01795 0.00831 -0.0201 1.0000 1.0000
-1.750 -0.1042 0.01790 0.00800 -0.0178 1.0000 1.0000
-1.500 -0.0905 0.01788 0.00774 -0.0156 1.0000 1.0000
-1.250 -0.0762 0.01789 0.00746 -0.0134 1.0000 1.0000
-1.000 -0.0616 0.01793 0.00729 -0.0113 1.0000 1.0000
-0.750 -0.0468 0.01799 0.00718 -0.0093 1.0000 1.0000
-0.500 -0.0317 0.01807 0.00711 -0.0073 1.0000 1.0000
-0.250 -0.0164 0.01818 0.00708 -0.0054 1.0000 1.0000
0.000 -0.0010 0.01831 0.00710 -0.0036 1.0000 1.0000
0.250 0.0144 0.01848 0.00711 -0.0018 1.0000 1.0000
0.500 0.0299 0.01867 0.00722 0.0000 1.0000 1.0000
0.750 0.0454 0.01890 0.00738 0.0016 1.0000 1.0000
1.000 0.0785 0.01931 0.00775 -0.0003 0.9938 1.0000
1.250 0.1231 0.01979 0.00823 -0.0045 0.9825 1.0000
1.500 0.1675 0.02023 0.00871 -0.0086 0.9704 1.0000
1.750 0.2119 0.02062 0.00915 -0.0125 0.9572 1.0000
2.000 0.2567 0.02093 0.00957 -0.0163 0.9432 1.0000
2.250 0.2990 0.02114 0.00990 -0.0194 0.9274 1.0000
2.500 0.3388 0.02125 0.01022 -0.0219 0.9094 1.0000
2.750 0.3831 0.02124 0.01041 -0.0249 0.8912 1.0000
3.000 0.4189 0.02114 0.01051 -0.0262 0.8690 1.0000
3.250 0.4543 0.02091 0.01052 -0.0270 0.8448 1.0000
3.500 0.4865 0.02059 0.01056 -0.0269 0.8172 1.0000
3.750 0.5201 0.02016 0.01040 -0.0268 0.7861 1.0000
4.000 0.5543 0.01975 0.01022 -0.0266 0.7470 1.0000
4.250 0.5906 0.01935 0.00999 -0.0264 0.6952 1.0000
4.500 0.6240 0.01921 0.00995 -0.0256 0.6266 1.0000
4.750 0.6479 0.01954 0.01009 -0.0236 0.5493 1.0000
5.000 0.6658 0.02020 0.01049 -0.0210 0.4713 1.0000
5.250 0.6802 0.02107 0.01106 -0.0182 0.3956 1.0000
5.500 0.6936 0.02208 0.01179 -0.0156 0.3233 1.0000
5.750 0.7069 0.02324 0.01267 -0.0132 0.2555 1.0000
6.000 0.7210 0.02456 0.01371 -0.0111 0.1959 1.0000
6.250 0.7365 0.02606 0.01500 -0.0093 0.1467 1.0000
6.500 0.7529 0.02763 0.01643 -0.0077 0.1096 1.0000
6.750 0.7700 0.02941 0.01814 -0.0061 0.0888 1.0000
7.000 0.7893 0.03122 0.02009 -0.0045 0.0724 1.0000
7.250 0.8072 0.03298 0.02219 -0.0029 0.0596 1.0000
7.500 0.8279 0.03528 0.02470 -0.0015 0.0529 1.0000
7.750 0.8499 0.03840 0.02816 -0.0002 0.0486 1.0000
8.000 0.8653 0.04110 0.03133 0.0018 0.0429 1.0000
8.250 0.8745 0.04359 0.03400 0.0038 0.0374 1.0000
8.500 0.8827 0.04724 0.03826 0.0063 0.0353 1.0000
8.750 0.8854 0.05107 0.04262 0.0091 0.0340 1.0000
9.000 0.8833 0.05488 0.04685 0.0119 0.0333 1.0000
9.250 0.8760 0.05875 0.05109 0.0146 0.0327 1.0000
9.500 0.8649 0.06254 0.05517 0.0171 0.0325 1.0000
9.750 0.8487 0.06614 0.05899 0.0197 0.0326 1.0000
10.000 0.8303 0.06995 0.06296 0.0213 0.0328 1.0000
10.250 0.8105 0.07439 0.06754 0.0212 0.0331 1.0000
10.500 0.7923 0.07939 0.07263 0.0195 0.0337 1.0000
10.750 0.7736 0.08559 0.07888 0.0158 0.0342 1.0000
11.000 0.7574 0.09289 0.08620 0.0109 0.0348 1.0000
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Polar data table (+)
Polar graphs
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