MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 200,000 Max Cl/Cd: 58.65 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh62-il-200000-n5.txt Download as CSV file: xf-mh62-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5812 0.08832 0.08510 0.0066 1.0000 0.0070
-9.000 -0.5845 0.08312 0.07994 0.0035 1.0000 0.0068
-8.750 -0.5907 0.07711 0.07398 -0.0004 1.0000 0.0068
-8.500 -0.5995 0.07037 0.06730 -0.0055 1.0000 0.0067
-8.250 -0.6101 0.06191 0.05885 -0.0138 1.0000 0.0065
-8.000 -0.6202 0.05373 0.05046 -0.0195 1.0000 0.0064
-7.750 -0.6238 0.04748 0.04393 -0.0223 1.0000 0.0063
-7.500 -0.6225 0.04146 0.03749 -0.0238 1.0000 0.0062
-7.250 -0.6139 0.03653 0.03210 -0.0243 1.0000 0.0061
-7.000 -0.6007 0.03211 0.02715 -0.0242 1.0000 0.0062
-6.750 -0.5831 0.02853 0.02305 -0.0239 1.0000 0.0062
-6.500 -0.5600 0.02551 0.01953 -0.0241 0.9782 0.0064
-6.250 -0.5313 0.02303 0.01657 -0.0247 0.9529 0.0066
-6.000 -0.5054 0.02130 0.01449 -0.0244 0.9345 0.0069
-5.750 -0.4831 0.01965 0.01261 -0.0236 0.9190 0.0078
-5.500 -0.4596 0.01903 0.01189 -0.0229 0.9056 0.0090
-5.250 -0.4360 0.01824 0.01093 -0.0220 0.8935 0.0103
-5.000 -0.4129 0.01722 0.00971 -0.0208 0.8825 0.0110
-4.750 -0.3899 0.01632 0.00864 -0.0197 0.8723 0.0115
-4.500 -0.3672 0.01518 0.00737 -0.0186 0.8621 0.0128
-4.250 -0.3426 0.01451 0.00656 -0.0178 0.8525 0.0149
-4.000 -0.3179 0.01387 0.00578 -0.0169 0.8436 0.0206
-3.750 -0.2932 0.01314 0.00508 -0.0162 0.8343 0.0415
-3.500 -0.2695 0.01221 0.00457 -0.0157 0.8252 0.1219
-3.250 -0.2450 0.01166 0.00423 -0.0151 0.8168 0.1944
-3.000 -0.2192 0.01129 0.00397 -0.0147 0.8075 0.2462
-2.750 -0.1939 0.01091 0.00377 -0.0143 0.7986 0.3108
-2.500 -0.1686 0.01060 0.00358 -0.0136 0.7903 0.3654
-2.250 -0.1426 0.01032 0.00341 -0.0132 0.7807 0.4147
-2.000 -0.1168 0.01008 0.00323 -0.0127 0.7717 0.4631
-1.750 -0.0914 0.00984 0.00309 -0.0120 0.7630 0.5119
-1.500 -0.0656 0.00960 0.00297 -0.0114 0.7531 0.5637
-1.250 -0.0404 0.00936 0.00287 -0.0106 0.7437 0.6200
-1.000 -0.0159 0.00911 0.00277 -0.0095 0.7347 0.6822
-0.750 0.0091 0.00885 0.00271 -0.0084 0.7244 0.7528
-0.500 0.0375 0.00863 0.00268 -0.0079 0.7143 0.8320
-0.250 0.0806 0.00853 0.00263 -0.0105 0.7035 0.9080
0.000 0.1271 0.00852 0.00253 -0.0141 0.6918 0.9569
0.250 0.1683 0.00853 0.00244 -0.0168 0.6793 0.9863
0.500 0.2039 0.00856 0.00237 -0.0184 0.6661 1.0000
0.750 0.2296 0.00861 0.00232 -0.0179 0.6527 1.0000
1.000 0.2555 0.00867 0.00229 -0.0174 0.6386 1.0000
1.250 0.2814 0.00873 0.00227 -0.0170 0.6238 1.0000
1.500 0.3074 0.00881 0.00228 -0.0165 0.6077 1.0000
1.750 0.3335 0.00890 0.00229 -0.0161 0.5906 1.0000
2.000 0.3596 0.00900 0.00231 -0.0157 0.5725 1.0000
2.250 0.3857 0.00913 0.00234 -0.0153 0.5536 1.0000
2.500 0.4119 0.00927 0.00240 -0.0149 0.5332 1.0000
2.750 0.4380 0.00943 0.00250 -0.0145 0.5124 1.0000
3.000 0.4642 0.00961 0.00260 -0.0142 0.4904 1.0000
3.250 0.4903 0.00981 0.00271 -0.0138 0.4684 1.0000
3.500 0.5164 0.01003 0.00287 -0.0135 0.4459 1.0000
3.750 0.5426 0.01026 0.00304 -0.0132 0.4235 1.0000
4.000 0.5686 0.01052 0.00323 -0.0129 0.4015 1.0000
4.250 0.5946 0.01078 0.00344 -0.0127 0.3796 1.0000
4.500 0.6205 0.01107 0.00370 -0.0124 0.3578 1.0000
4.750 0.6464 0.01138 0.00395 -0.0122 0.3363 1.0000
5.000 0.6722 0.01169 0.00423 -0.0119 0.3150 1.0000
5.250 0.6977 0.01204 0.00454 -0.0116 0.2934 1.0000
5.500 0.7233 0.01239 0.00487 -0.0114 0.2719 1.0000
6.000 0.7736 0.01319 0.00564 -0.0108 0.2294 1.0000
6.250 0.7984 0.01365 0.00606 -0.0105 0.2088 1.0000
6.500 0.8231 0.01411 0.00650 -0.0102 0.1883 1.0000
7.000 0.8714 0.01515 0.00751 -0.0096 0.1506 1.0000
7.250 0.8951 0.01572 0.00811 -0.0092 0.1324 1.0000
7.750 0.9412 0.01698 0.00934 -0.0083 0.0978 1.0000
8.000 0.9635 0.01767 0.01003 -0.0079 0.0814 1.0000
8.250 0.9852 0.01843 0.01078 -0.0073 0.0667 1.0000
8.500 1.0060 0.01930 0.01163 -0.0067 0.0529 1.0000
8.750 1.0259 0.02024 0.01258 -0.0060 0.0411 1.0000
9.000 1.0452 0.02121 0.01361 -0.0052 0.0326 1.0000
9.250 1.0634 0.02227 0.01481 -0.0043 0.0260 1.0000
9.500 1.0785 0.02362 0.01619 -0.0032 0.0207 1.0000
9.750 1.0956 0.02464 0.01735 -0.0023 0.0169 1.0000
10.000 1.1065 0.02624 0.01902 -0.0009 0.0135 1.0000
10.250 1.1207 0.02738 0.02032 0.0002 0.0111 1.0000
10.500 1.1305 0.02881 0.02184 0.0016 0.0093 1.0000
10.750 1.1298 0.03078 0.02397 0.0039 0.0083 1.0000
11.000 1.1310 0.03256 0.02592 0.0058 0.0078 1.0000
11.250 1.1308 0.03468 0.02822 0.0072 0.0070 1.0000
11.500 1.1302 0.03701 0.03071 0.0080 0.0067 1.0000
11.750 1.1288 0.03960 0.03346 0.0084 0.0063 1.0000
12.000 1.1268 0.04244 0.03644 0.0084 0.0059 1.0000
12.250 1.1237 0.04556 0.03971 0.0080 0.0057 1.0000
12.500 1.1189 0.04909 0.04340 0.0072 0.0056 1.0000
12.750 1.1094 0.05347 0.04796 0.0055 0.0053 1.0000
13.000 1.0998 0.05815 0.05281 0.0037 0.0052 1.0000
13.250 1.0932 0.06264 0.05745 0.0016 0.0052 1.0000
13.500 1.0842 0.06789 0.06290 -0.0012 0.0046 1.0000
13.750 1.0707 0.07389 0.06904 -0.0041 0.0048 1.0000
14.000 1.0597 0.07991 0.07523 -0.0074 0.0047 1.0000
14.250 1.0441 0.08688 0.08235 -0.0110 0.0049 1.0000
14.500 1.0347 0.09331 0.08895 -0.0149 0.0047 1.0000
14.750 1.0198 0.10095 0.09674 -0.0191 0.0046 1.0000
15.000 1.0058 0.10858 0.10449 -0.0233 0.0047 1.0000
15.250 0.9901 0.11670 0.11273 -0.0277 0.0049 1.0000
15.500 0.9749 0.12498 0.12106 -0.0320 0.0050 1.0000
15.750 0.9611 0.13378 0.12998 -0.0370 0.0049 1.0000
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Polar data table (+)
Polar graphs
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