MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 200,000 Max Cl/Cd: 63.87 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh61-il-200000.txt Download as CSV file: xf-mh61-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5041 0.15616 0.15337 0.0366 1.0000 0.0305
-13.000 -0.4999 0.15342 0.15062 0.0351 1.0000 0.0313
-6.250 -0.5205 0.03145 0.02593 -0.0298 0.9476 0.0259
-6.000 -0.5060 0.02775 0.02180 -0.0278 0.9348 0.0229
-5.750 -0.4877 0.02444 0.01783 -0.0250 0.9240 0.0195
-5.500 -0.4669 0.02311 0.01613 -0.0228 0.9144 0.0182
-5.250 -0.4446 0.02181 0.01461 -0.0212 0.9049 0.0178
-5.000 -0.4222 0.02028 0.01290 -0.0198 0.8963 0.0177
-4.750 -0.4023 0.01871 0.01119 -0.0178 0.8887 0.0179
-4.500 -0.3810 0.01708 0.00948 -0.0165 0.8801 0.0190
-4.250 -0.3606 0.01610 0.00841 -0.0148 0.8727 0.0210
-4.000 -0.3369 0.01554 0.00774 -0.0138 0.8648 0.0273
-3.750 -0.3220 0.01302 0.00601 -0.0116 0.8574 0.1867
-3.500 -0.3042 0.01204 0.00582 -0.0100 0.8501 0.3702
-3.250 -0.2820 0.01166 0.00571 -0.0089 0.8427 0.4562
-3.000 -0.2598 0.01138 0.00555 -0.0075 0.8360 0.5147
-2.750 -0.2364 0.01109 0.00543 -0.0064 0.8285 0.5740
-2.500 -0.2142 0.01082 0.00528 -0.0048 0.8221 0.6290
-2.250 -0.1904 0.01055 0.00516 -0.0037 0.8145 0.6883
-2.000 -0.1677 0.01028 0.00505 -0.0019 0.8083 0.7519
-1.750 -0.1399 0.01008 0.00503 -0.0013 0.8008 0.8218
-1.500 -0.1011 0.01001 0.00497 -0.0025 0.7949 0.8869
-1.250 -0.0514 0.01008 0.00495 -0.0064 0.7877 0.9292
-1.000 -0.0044 0.01015 0.00488 -0.0098 0.7814 0.9561
-0.750 0.0451 0.01023 0.00484 -0.0140 0.7736 0.9751
-0.500 0.0938 0.01023 0.00467 -0.0182 0.7671 0.9924
-0.250 0.1337 0.01016 0.00453 -0.0210 0.7583 1.0000
0.000 0.1555 0.01012 0.00437 -0.0199 0.7509 1.0000
0.250 0.1790 0.01010 0.00428 -0.0192 0.7420 1.0000
0.500 0.2029 0.01010 0.00422 -0.0186 0.7335 1.0000
0.750 0.2260 0.01009 0.00411 -0.0175 0.7259 1.0000
1.000 0.2511 0.01010 0.00410 -0.0171 0.7162 1.0000
1.250 0.2756 0.01012 0.00406 -0.0164 0.7076 1.0000
1.500 0.2999 0.01012 0.00401 -0.0156 0.6991 1.0000
1.750 0.3254 0.01015 0.00402 -0.0151 0.6889 1.0000
2.000 0.3506 0.01018 0.00401 -0.0145 0.6793 1.0000
2.250 0.3753 0.01019 0.00395 -0.0137 0.6705 1.0000
2.500 0.4011 0.01022 0.00399 -0.0133 0.6593 1.0000
2.750 0.4269 0.01025 0.00405 -0.0128 0.6479 1.0000
3.000 0.4526 0.01029 0.00409 -0.0123 0.6365 1.0000
3.250 0.4783 0.01034 0.00412 -0.0118 0.6246 1.0000
3.500 0.5041 0.01038 0.00417 -0.0112 0.6120 1.0000
3.750 0.5300 0.01044 0.00426 -0.0107 0.5983 1.0000
4.000 0.5559 0.01051 0.00433 -0.0103 0.5833 1.0000
4.250 0.5818 0.01058 0.00442 -0.0098 0.5671 1.0000
4.500 0.6076 0.01068 0.00450 -0.0093 0.5500 1.0000
4.750 0.6335 0.01080 0.00468 -0.0088 0.5308 1.0000
5.000 0.6593 0.01094 0.00483 -0.0084 0.5102 1.0000
5.250 0.6850 0.01112 0.00502 -0.0080 0.4878 1.0000
5.500 0.7105 0.01135 0.00523 -0.0075 0.4640 1.0000
5.750 0.7357 0.01161 0.00548 -0.0071 0.4378 1.0000
6.000 0.7607 0.01191 0.00578 -0.0067 0.4077 1.0000
6.250 0.7851 0.01230 0.00617 -0.0063 0.3734 1.0000
6.500 0.8090 0.01275 0.00658 -0.0059 0.3355 1.0000
6.750 0.8318 0.01336 0.00707 -0.0055 0.2900 1.0000
7.000 0.8530 0.01419 0.00769 -0.0050 0.2281 1.0000
7.250 0.8704 0.01554 0.00860 -0.0043 0.1480 1.0000
7.500 0.8841 0.01735 0.00996 -0.0032 0.0815 1.0000
7.750 0.8966 0.01920 0.01160 -0.0017 0.0486 1.0000
8.000 0.9097 0.02082 0.01320 -0.0001 0.0329 1.0000
8.250 0.9195 0.02272 0.01517 0.0020 0.0256 1.0000
8.500 0.9281 0.02465 0.01709 0.0039 0.0199 1.0000
8.750 0.9419 0.02615 0.01872 0.0056 0.0174 1.0000
9.000 0.9554 0.02797 0.02067 0.0074 0.0157 1.0000
9.250 0.9700 0.02993 0.02284 0.0090 0.0148 1.0000
9.500 0.9848 0.03211 0.02521 0.0105 0.0143 1.0000
9.750 0.9977 0.03463 0.02797 0.0121 0.0139 1.0000
10.000 1.0077 0.03749 0.03112 0.0137 0.0139 1.0000
10.250 1.0128 0.04065 0.03462 0.0157 0.0141 1.0000
10.500 1.0088 0.04397 0.03830 0.0182 0.0145 1.0000
10.750 0.9994 0.04745 0.04209 0.0203 0.0149 1.0000
11.000 0.9870 0.05114 0.04607 0.0216 0.0151 1.0000
11.250 0.9722 0.05526 0.05045 0.0220 0.0156 1.0000
11.500 0.9569 0.05959 0.05501 0.0217 0.0159 1.0000
11.750 0.9407 0.06428 0.05990 0.0204 0.0161 1.0000
12.000 0.9226 0.06956 0.06538 0.0183 0.0164 1.0000
12.250 0.9035 0.07549 0.07147 0.0152 0.0165 1.0000
12.500 0.8840 0.08206 0.07820 0.0112 0.0167 1.0000
12.750 0.8636 0.08957 0.08585 0.0062 0.0167 1.0000
13.000 0.8433 0.09794 0.09434 0.0006 0.0168 1.0000
13.250 0.8230 0.10750 0.10399 -0.0057 0.0171 1.0000
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Polar data table (+)
Polar graphs
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