MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 200,000 Max Cl/Cd: 64.97 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh104-il-200000-n5.txt Download as CSV file: xf-mh104-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6743 0.10958 0.10580 -0.0048 1.0000 0.0099
-14.250 -0.7341 0.09133 0.08721 -0.0163 1.0000 0.0095
-14.000 -0.7646 0.08121 0.07682 -0.0229 1.0000 0.0093
-13.750 -0.7863 0.07346 0.06885 -0.0279 1.0000 0.0092
-13.500 -0.8010 0.06737 0.06259 -0.0318 1.0000 0.0093
-13.250 -0.8156 0.06155 0.05656 -0.0353 1.0000 0.0092
-13.000 -0.8266 0.05665 0.05145 -0.0380 1.0000 0.0091
-12.750 -0.8341 0.05260 0.04727 -0.0399 1.0000 0.0092
-12.500 -0.8406 0.04888 0.04337 -0.0413 1.0000 0.0092
-12.250 -0.8455 0.04563 0.03997 -0.0420 1.0000 0.0093
-12.000 -0.8483 0.04284 0.03704 -0.0422 1.0000 0.0094
-11.750 -0.8490 0.04042 0.03447 -0.0419 1.0000 0.0094
-11.500 -0.8488 0.03818 0.03209 -0.0411 1.0000 0.0095
-11.250 -0.8469 0.03625 0.03003 -0.0399 1.0000 0.0097
-11.000 -0.8436 0.03447 0.02811 -0.0384 1.0000 0.0098
-10.750 -0.8391 0.03285 0.02637 -0.0366 1.0000 0.0100
-10.500 -0.8326 0.03141 0.02482 -0.0346 1.0000 0.0101
-10.250 -0.8261 0.03000 0.02330 -0.0324 1.0000 0.0104
-10.000 -0.8183 0.02875 0.02196 -0.0301 1.0000 0.0106
-9.750 -0.8091 0.02752 0.02062 -0.0279 1.0000 0.0110
-9.500 -0.7973 0.02638 0.01938 -0.0260 1.0000 0.0112
-9.250 -0.7844 0.02529 0.01819 -0.0242 1.0000 0.0115
-9.000 -0.7554 0.02394 0.01673 -0.0258 0.9154 0.0120
-8.750 -0.7347 0.02304 0.01567 -0.0251 0.8707 0.0127
-8.500 -0.7181 0.02234 0.01479 -0.0234 0.8396 0.0136
-8.250 -0.7012 0.02169 0.01393 -0.0216 0.8150 0.0147
-8.000 -0.6851 0.02092 0.01306 -0.0198 0.7935 0.0157
-7.750 -0.6664 0.02031 0.01229 -0.0183 0.7749 0.0173
-7.500 -0.6479 0.01962 0.01143 -0.0168 0.7577 0.0189
-7.250 -0.6287 0.01895 0.01063 -0.0154 0.7418 0.0212
-7.000 -0.6083 0.01833 0.00990 -0.0141 0.7271 0.0245
-6.750 -0.5875 0.01772 0.00920 -0.0129 0.7130 0.0305
-6.500 -0.5666 0.01708 0.00851 -0.0118 0.6998 0.0401
-6.250 -0.5458 0.01640 0.00786 -0.0106 0.6874 0.0589
-6.000 -0.5260 0.01560 0.00722 -0.0095 0.6756 0.0983
-5.750 -0.5058 0.01484 0.00672 -0.0084 0.6637 0.1552
-5.500 -0.4833 0.01437 0.00638 -0.0076 0.6522 0.2013
-5.250 -0.4594 0.01407 0.00609 -0.0069 0.6413 0.2323
-5.000 -0.4348 0.01382 0.00584 -0.0062 0.6305 0.2584
-4.750 -0.4102 0.01358 0.00562 -0.0056 0.6205 0.2853
-4.500 -0.3855 0.01339 0.00541 -0.0050 0.6110 0.3115
-4.250 -0.3601 0.01321 0.00522 -0.0044 0.6009 0.3326
-4.000 -0.3344 0.01306 0.00502 -0.0040 0.5915 0.3493
-3.750 -0.3085 0.01293 0.00482 -0.0035 0.5823 0.3648
-3.500 -0.2824 0.01279 0.00464 -0.0031 0.5736 0.3799
-3.250 -0.2564 0.01268 0.00447 -0.0026 0.5657 0.3956
-3.000 -0.2301 0.01255 0.00433 -0.0022 0.5575 0.4115
-2.750 -0.2040 0.01245 0.00418 -0.0018 0.5500 0.4282
-2.500 -0.1777 0.01234 0.00406 -0.0014 0.5419 0.4457
-2.250 -0.1517 0.01225 0.00394 -0.0009 0.5347 0.4641
-2.000 -0.1255 0.01214 0.00384 -0.0005 0.5277 0.4833
-1.750 -0.0996 0.01204 0.00376 0.0000 0.5212 0.5042
-1.500 -0.0736 0.01195 0.00369 0.0004 0.5153 0.5265
-1.250 -0.0478 0.01185 0.00364 0.0009 0.5088 0.5507
-1.000 -0.0222 0.01178 0.00359 0.0015 0.5032 0.5770
-0.750 0.0036 0.01168 0.00358 0.0020 0.4970 0.6055
-0.500 0.0293 0.01161 0.00357 0.0026 0.4915 0.6356
0.000 0.0811 0.01148 0.00361 0.0038 0.4817 0.7003
0.250 0.1076 0.01144 0.00365 0.0043 0.4766 0.7338
0.500 0.1349 0.01144 0.00370 0.0046 0.4722 0.7677
0.750 0.1643 0.01145 0.00380 0.0046 0.4670 0.8001
1.000 0.1960 0.01150 0.00391 0.0041 0.4622 0.8309
1.250 0.2308 0.01161 0.00402 0.0029 0.4580 0.8576
1.500 0.2674 0.01174 0.00415 0.0013 0.4535 0.8799
1.750 0.3052 0.01188 0.00430 -0.0005 0.4484 0.8978
2.000 0.3420 0.01204 0.00443 -0.0023 0.4441 0.9127
2.250 0.3774 0.01221 0.00454 -0.0037 0.4403 0.9260
2.500 0.4137 0.01236 0.00470 -0.0054 0.4354 0.9373
2.750 0.4509 0.01251 0.00485 -0.0073 0.4308 0.9460
3.000 0.4841 0.01269 0.00497 -0.0083 0.4269 0.9559
3.250 0.5212 0.01285 0.00512 -0.0103 0.4225 0.9633
3.500 0.5563 0.01299 0.00530 -0.0119 0.4178 0.9712
3.750 0.5932 0.01313 0.00542 -0.0138 0.4134 0.9781
4.000 0.6298 0.01329 0.00554 -0.0157 0.4095 0.9844
4.250 0.6681 0.01340 0.00572 -0.0181 0.4044 0.9902
4.500 0.7064 0.01351 0.00585 -0.0204 0.3996 0.9956
4.750 0.7438 0.01364 0.00595 -0.0226 0.3954 1.0000
5.000 0.7662 0.01378 0.00615 -0.0218 0.3911 1.0000
5.250 0.7887 0.01392 0.00634 -0.0210 0.3865 1.0000
5.500 0.8111 0.01407 0.00650 -0.0201 0.3822 1.0000
5.750 0.8336 0.01425 0.00668 -0.0192 0.3781 1.0000
6.000 0.8560 0.01442 0.00694 -0.0184 0.3728 1.0000
6.250 0.8783 0.01458 0.00714 -0.0175 0.3678 1.0000
6.500 0.9006 0.01478 0.00734 -0.0166 0.3631 1.0000
6.750 0.9228 0.01496 0.00762 -0.0157 0.3570 1.0000
7.000 0.9448 0.01515 0.00784 -0.0147 0.3514 1.0000
7.250 0.9668 0.01536 0.00812 -0.0138 0.3455 1.0000
7.500 0.9885 0.01557 0.00839 -0.0129 0.3390 1.0000
7.750 1.0100 0.01579 0.00864 -0.0118 0.3327 1.0000
8.000 1.0314 0.01602 0.00898 -0.0109 0.3252 1.0000
8.250 1.0521 0.01627 0.00926 -0.0098 0.3182 1.0000
8.500 1.0728 0.01653 0.00961 -0.0087 0.3096 1.0000
8.750 1.0928 0.01682 0.00994 -0.0075 0.3013 1.0000
9.000 1.1119 0.01713 0.01030 -0.0062 0.2917 1.0000
9.250 1.1307 0.01747 0.01072 -0.0049 0.2814 1.0000
9.500 1.1482 0.01786 0.01114 -0.0035 0.2706 1.0000
9.750 1.1640 0.01832 0.01161 -0.0018 0.2591 1.0000
10.000 1.1778 0.01885 0.01214 0.0001 0.2472 1.0000
10.250 1.1905 0.01944 0.01275 0.0021 0.2347 1.0000
10.500 1.2012 0.02009 0.01342 0.0043 0.2227 1.0000
10.750 1.2092 0.02083 0.01417 0.0068 0.2109 1.0000
11.000 1.2123 0.02165 0.01499 0.0099 0.2004 1.0000
11.500 1.2122 0.02377 0.01713 0.0158 0.1802 1.0000
11.750 1.2124 0.02518 0.01857 0.0178 0.1706 1.0000
12.000 1.2106 0.02695 0.02035 0.0194 0.1614 1.0000
12.250 1.2106 0.02882 0.02226 0.0204 0.1519 1.0000
12.500 1.2097 0.03092 0.02440 0.0212 0.1436 1.0000
12.750 1.2058 0.03342 0.02691 0.0216 0.1357 1.0000
13.000 1.2047 0.03582 0.02936 0.0219 0.1276 1.0000
13.250 1.1994 0.03869 0.03225 0.0220 0.1208 1.0000
13.500 1.1967 0.04141 0.03503 0.0219 0.1134 1.0000
13.750 1.1905 0.04455 0.03820 0.0217 0.1073 1.0000
14.000 1.1866 0.04753 0.04123 0.0214 0.1008 1.0000
14.250 1.1793 0.05093 0.04466 0.0210 0.0956 1.0000
14.500 1.1755 0.05404 0.04783 0.0205 0.0893 1.0000
14.750 1.1677 0.05773 0.05154 0.0197 0.0843 1.0000
15.000 1.1648 0.06095 0.05485 0.0191 0.0790 1.0000
15.250 1.1587 0.06466 0.05860 0.0181 0.0743 1.0000
15.500 1.1538 0.06827 0.06227 0.0172 0.0699 1.0000
15.750 1.1489 0.07199 0.06605 0.0161 0.0652 1.0000
16.000 1.1408 0.07620 0.07029 0.0148 0.0613 1.0000
16.250 1.1373 0.07986 0.07402 0.0137 0.0567 1.0000
16.500 1.1308 0.08403 0.07825 0.0123 0.0533 1.0000
16.750 1.1242 0.08827 0.08254 0.0109 0.0499 1.0000
17.000 1.1187 0.09243 0.08676 0.0094 0.0462 1.0000
17.250 1.1110 0.09700 0.09138 0.0077 0.0436 1.0000
17.500 1.1050 0.10140 0.09586 0.0061 0.0409 1.0000
17.750 1.0993 0.10577 0.10031 0.0043 0.0382 1.0000
18.000 1.0918 0.11054 0.10513 0.0024 0.0360 1.0000
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Polar data table (+)
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