MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 200,000 Max Cl/Cd: 60.63 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh45-il-200000.txt Download as CSV file: xf-mh45-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5569 0.10130 0.09816 0.0135 1.0000 0.0440
-9.000 -0.5601 0.09614 0.09305 0.0093 1.0000 0.0461
-7.750 -0.5964 0.06523 0.06220 -0.0176 1.0000 0.0499
-7.500 -0.5843 0.06268 0.05968 -0.0176 1.0000 0.0514
-7.250 -0.5763 0.05879 0.05572 -0.0195 1.0000 0.0532
-7.000 -0.5692 0.05388 0.05062 -0.0223 1.0000 0.0565
-6.750 -0.5667 0.04766 0.04391 -0.0254 1.0000 0.0623
-6.500 -0.5465 0.04479 0.04108 -0.0260 1.0000 0.0648
-6.250 -0.5345 0.03110 0.02576 -0.0247 1.0000 0.0257
-6.000 -0.5180 0.02626 0.02019 -0.0236 1.0000 0.0219
-5.750 -0.4838 0.02406 0.01741 -0.0246 0.9853 0.0204
-5.500 -0.4469 0.02164 0.01464 -0.0265 0.9724 0.0204
-5.250 -0.4144 0.01911 0.01192 -0.0274 0.9594 0.0211
-5.000 -0.3863 0.01799 0.01076 -0.0276 0.9452 0.0235
-4.750 -0.3616 0.01739 0.01004 -0.0265 0.9310 0.0267
-4.500 -0.3414 0.01604 0.00861 -0.0247 0.9177 0.0287
-4.250 -0.3213 0.01509 0.00763 -0.0229 0.9052 0.0325
-4.000 -0.3004 0.01417 0.00663 -0.0211 0.8937 0.0432
-3.750 -0.2834 0.01232 0.00555 -0.0191 0.8832 0.1869
-3.500 -0.2622 0.01184 0.00538 -0.0178 0.8730 0.2808
-3.250 -0.2385 0.01153 0.00522 -0.0168 0.8624 0.3388
-3.000 -0.2153 0.01125 0.00507 -0.0157 0.8526 0.3949
-2.750 -0.1934 0.01095 0.00494 -0.0142 0.8438 0.4616
-2.500 -0.1698 0.01062 0.00482 -0.0131 0.8334 0.5288
-2.250 -0.1470 0.01031 0.00471 -0.0118 0.8239 0.5948
-2.000 -0.1251 0.01000 0.00460 -0.0099 0.8155 0.6657
-1.750 -0.1021 0.00967 0.00453 -0.0083 0.8053 0.7466
-1.500 -0.0758 0.00942 0.00449 -0.0069 0.7963 0.8376
-1.250 -0.0286 0.00934 0.00441 -0.0098 0.7877 0.9187
-1.000 0.0249 0.00936 0.00431 -0.0145 0.7775 0.9624
-0.750 0.0759 0.00937 0.00416 -0.0189 0.7678 0.9907
-0.500 0.1120 0.00934 0.00395 -0.0205 0.7581 1.0000
-0.250 0.1359 0.00933 0.00384 -0.0198 0.7465 1.0000
0.000 0.1601 0.00934 0.00375 -0.0190 0.7353 1.0000
0.250 0.1843 0.00935 0.00365 -0.0182 0.7245 1.0000
0.500 0.2085 0.00937 0.00354 -0.0172 0.7139 1.0000
0.750 0.2336 0.00939 0.00349 -0.0166 0.7015 1.0000
1.000 0.2589 0.00942 0.00344 -0.0159 0.6889 1.0000
1.250 0.2844 0.00945 0.00340 -0.0153 0.6760 1.0000
1.500 0.3099 0.00949 0.00336 -0.0146 0.6628 1.0000
1.750 0.3356 0.00953 0.00334 -0.0140 0.6490 1.0000
2.000 0.3613 0.00958 0.00332 -0.0134 0.6345 1.0000
2.250 0.3872 0.00964 0.00333 -0.0128 0.6194 1.0000
2.500 0.4131 0.00972 0.00333 -0.0122 0.6036 1.0000
2.750 0.4391 0.00980 0.00335 -0.0117 0.5873 1.0000
3.000 0.4650 0.00992 0.00337 -0.0111 0.5706 1.0000
3.250 0.4913 0.01003 0.00347 -0.0107 0.5518 1.0000
3.500 0.5175 0.01017 0.00356 -0.0103 0.5328 1.0000
3.750 0.5435 0.01034 0.00365 -0.0098 0.5141 1.0000
4.000 0.5698 0.01052 0.00380 -0.0094 0.4940 1.0000
4.250 0.5959 0.01073 0.00395 -0.0091 0.4740 1.0000
4.500 0.6219 0.01097 0.00412 -0.0087 0.4541 1.0000
4.750 0.6480 0.01120 0.00434 -0.0084 0.4330 1.0000
5.000 0.6737 0.01150 0.00457 -0.0080 0.4127 1.0000
5.250 0.6997 0.01177 0.00484 -0.0077 0.3903 1.0000
5.500 0.7252 0.01210 0.00510 -0.0074 0.3689 1.0000
5.750 0.7508 0.01243 0.00541 -0.0071 0.3455 1.0000
6.000 0.7760 0.01280 0.00577 -0.0068 0.3223 1.0000
6.250 0.8008 0.01323 0.00613 -0.0064 0.2984 1.0000
6.500 0.8257 0.01366 0.00654 -0.0061 0.2735 1.0000
6.750 0.8500 0.01417 0.00700 -0.0058 0.2491 1.0000
7.000 0.8737 0.01475 0.00753 -0.0054 0.2256 1.0000
7.250 0.8972 0.01536 0.00810 -0.0050 0.2033 1.0000
7.500 0.9199 0.01606 0.00873 -0.0046 0.1833 1.0000
7.750 0.9427 0.01674 0.00940 -0.0041 0.1648 1.0000
8.000 0.9647 0.01749 0.01013 -0.0035 0.1487 1.0000
8.250 0.9862 0.01828 0.01093 -0.0030 0.1343 1.0000
8.500 1.0073 0.01910 0.01176 -0.0023 0.1214 1.0000
8.750 1.0278 0.01996 0.01265 -0.0016 0.1097 1.0000
9.000 1.0474 0.02090 0.01360 -0.0009 0.0991 1.0000
9.250 1.0657 0.02194 0.01464 0.0000 0.0896 1.0000
9.500 1.0843 0.02281 0.01556 0.0007 0.0804 1.0000
9.750 1.1020 0.02382 0.01671 0.0017 0.0720 1.0000
10.000 1.1165 0.02518 0.01807 0.0028 0.0650 1.0000
10.250 1.1323 0.02620 0.01923 0.0039 0.0586 1.0000
10.500 1.1437 0.02786 0.02092 0.0053 0.0531 1.0000
10.750 1.1561 0.02897 0.02217 0.0066 0.0479 1.0000
11.000 1.1636 0.03122 0.02436 0.0082 0.0437 1.0000
11.250 1.1705 0.03250 0.02589 0.0101 0.0412 1.0000
11.500 1.1756 0.03400 0.02753 0.0117 0.0383 1.0000
11.750 1.1796 0.03565 0.02921 0.0128 0.0358 1.0000
12.000 1.1825 0.03861 0.03231 0.0141 0.0335 1.0000
12.250 1.1841 0.04065 0.03459 0.0149 0.0319 1.0000
12.500 1.1849 0.04293 0.03706 0.0154 0.0302 1.0000
12.750 1.1848 0.04540 0.03966 0.0156 0.0286 1.0000
13.000 1.1847 0.04778 0.04208 0.0154 0.0270 1.0000
13.250 1.1781 0.05195 0.04639 0.0155 0.0257 1.0000
13.500 1.1682 0.05610 0.05079 0.0147 0.0251 1.0000
13.750 1.1589 0.06013 0.05506 0.0131 0.0244 1.0000
14.000 1.1483 0.06473 0.05988 0.0113 0.0239 1.0000
14.250 1.1364 0.06970 0.06505 0.0088 0.0231 1.0000
14.500 1.1261 0.07462 0.07013 0.0060 0.0221 1.0000
14.750 1.1095 0.08102 0.07673 0.0026 0.0221 1.0000
15.000 1.0884 0.08873 0.08466 -0.0018 0.0224 1.0000
15.250 1.0653 0.09740 0.09354 -0.0071 0.0228 1.0000
15.500 1.0433 0.10638 0.10268 -0.0129 0.0226 1.0000
15.750 1.0059 0.11932 0.11579 -0.0204 0.0247 1.0000
16.000 0.8420 0.17994 0.17633 -0.0519 0.0417 1.0000
16.250 0.8557 0.18228 0.17873 -0.0510 0.0444 1.0000
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Polar data table (+)
Polar graphs
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