MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 50,000 Max Cl/Cd: 11.99 at α=0° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh104-il-50000.txt Download as CSV file: xf-mh104-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5367 0.10157 0.09528 -0.0194 1.0000 0.1145
-10.750 -0.5375 0.09586 0.08963 -0.0213 1.0000 0.1135
-10.500 -0.6081 0.07918 0.07297 -0.0354 1.0000 0.1002
-10.250 -0.6269 0.07331 0.06709 -0.0380 1.0000 0.0989
-10.000 -0.6498 0.06831 0.06203 -0.0392 1.0000 0.0975
-9.750 -0.6753 0.06395 0.05755 -0.0383 1.0000 0.0962
-9.500 -0.6946 0.05967 0.05307 -0.0371 1.0000 0.0950
-9.250 -0.7085 0.05550 0.04860 -0.0354 1.0000 0.0942
-9.000 -0.7151 0.05162 0.04438 -0.0335 1.0000 0.0940
-8.750 -0.7150 0.04818 0.04060 -0.0315 1.0000 0.0954
-8.500 -0.7118 0.04506 0.03709 -0.0293 1.0000 0.0979
-8.250 -0.7072 0.04222 0.03372 -0.0268 1.0000 0.1006
-8.000 -0.6903 0.03943 0.03101 -0.0257 1.0000 0.1060
-7.750 -0.6773 0.03716 0.02852 -0.0237 1.0000 0.1120
-7.500 -0.6659 0.03519 0.02662 -0.0216 1.0000 0.1208
-7.250 -0.6608 0.03357 0.02490 -0.0183 1.0000 0.1304
-7.000 -0.6611 0.03256 0.02395 -0.0146 1.0000 0.1407
-6.750 -0.6629 0.03161 0.02314 -0.0107 1.0000 0.1533
-6.500 -0.6648 0.03062 0.02221 -0.0069 1.0000 0.1724
-6.250 -0.6664 0.02973 0.02154 -0.0032 1.0000 0.2005
-6.000 -0.6702 0.02896 0.02113 0.0010 1.0000 0.2464
-5.750 -0.6575 0.02895 0.02170 0.0028 0.9917 0.3291
-5.500 -0.6149 0.02996 0.02293 0.0004 0.9724 0.4054
-5.250 -0.5672 0.03076 0.02382 -0.0023 0.9553 0.4616
-5.000 -0.5201 0.03095 0.02399 -0.0049 0.9393 0.5020
-4.750 -0.4723 0.03076 0.02368 -0.0079 0.9240 0.5357
-4.500 -0.4239 0.03045 0.02323 -0.0111 0.9095 0.5661
-4.250 -0.3846 0.03011 0.02272 -0.0129 0.8949 0.5938
-4.000 -0.3473 0.02992 0.02243 -0.0141 0.8804 0.6201
-3.750 -0.3116 0.02983 0.02227 -0.0147 0.8663 0.6458
-3.500 -0.2826 0.02973 0.02205 -0.0146 0.8529 0.6724
-3.250 -0.2481 0.02982 0.02206 -0.0149 0.8402 0.6995
-3.000 -0.2068 0.03000 0.02215 -0.0158 0.8287 0.7282
-2.750 -0.1656 0.03027 0.02231 -0.0168 0.8174 0.7572
-2.500 -0.1294 0.03072 0.02266 -0.0174 0.8052 0.7860
-2.250 -0.0802 0.03126 0.02305 -0.0198 0.7940 0.8158
-2.000 -0.0135 0.03168 0.02325 -0.0247 0.7844 0.8457
-1.750 0.0659 0.03225 0.02359 -0.0327 0.7721 0.8718
-1.500 0.1343 0.03257 0.02372 -0.0399 0.7608 0.9001
-1.250 0.2020 0.03257 0.02353 -0.0472 0.7511 0.9296
-1.000 0.2705 0.03241 0.02320 -0.0556 0.7404 0.9597
-0.750 0.3437 0.03202 0.02269 -0.0660 0.7295 0.9896
-0.500 0.3786 0.03173 0.02226 -0.0692 0.7222 1.0000
-0.250 0.3851 0.03258 0.02310 -0.0694 0.7134 1.0000
0.000 0.3947 0.03293 0.02336 -0.0680 0.7072 1.0000
0.250 0.3973 0.03413 0.02456 -0.0674 0.6993 1.0000
0.500 0.4055 0.03482 0.02517 -0.0659 0.6930 1.0000
0.750 0.4060 0.03613 0.02645 -0.0643 0.6865 1.0000
1.000 0.4051 0.03746 0.02775 -0.0623 0.6800 1.0000
1.250 0.4200 0.03805 0.02823 -0.0605 0.6749 1.0000
1.500 0.3946 0.04058 0.03076 -0.0569 0.6690 1.0000
1.750 0.3890 0.04214 0.03226 -0.0539 0.6637 1.0000
2.000 0.4066 0.04298 0.03302 -0.0526 0.6585 1.0000
2.250 0.3696 0.04572 0.03568 -0.0472 0.6551 1.0000
2.500 0.3455 0.04782 0.03769 -0.0425 0.6521 1.0000
2.750 0.3306 0.04959 0.03936 -0.0384 0.6495 1.0000
3.000 0.3692 0.05058 0.04032 -0.0398 0.6429 1.0000
3.250 0.3448 0.05272 0.04237 -0.0352 0.6421 1.0000
3.500 0.3329 0.05474 0.04432 -0.0322 0.6416 1.0000
3.750 0.3305 0.05678 0.04630 -0.0304 0.6421 1.0000
4.000 0.3310 0.05889 0.04838 -0.0292 0.6439 1.0000
4.250 0.1733 0.06280 0.05226 -0.0213 0.8061 1.0000
4.500 0.1918 0.06460 0.05404 -0.0215 0.7913 1.0000
4.750 0.2103 0.06646 0.05587 -0.0217 0.7763 1.0000
5.000 0.2277 0.06838 0.05776 -0.0218 0.7627 1.0000
5.250 0.2468 0.07047 0.05984 -0.0221 0.7493 1.0000
5.500 0.2709 0.07299 0.06236 -0.0231 0.7364 1.0000
5.750 0.2967 0.07562 0.06501 -0.0242 0.7224 1.0000
6.250 0.3165 0.07859 0.06797 -0.0225 0.6934 1.0000
6.500 0.3259 0.08031 0.06969 -0.0218 0.6800 1.0000
6.750 0.3378 0.08235 0.07174 -0.0215 0.6678 1.0000
7.000 0.3573 0.08500 0.07442 -0.0220 0.6564 1.0000
7.250 0.3878 0.08839 0.07787 -0.0234 0.6435 1.0000
7.500 0.3880 0.08942 0.07891 -0.0219 0.6298 1.0000
7.750 0.3942 0.09121 0.08072 -0.0211 0.6166 1.0000
8.000 0.4036 0.09343 0.08297 -0.0208 0.6050 1.0000
8.250 0.4297 0.09699 0.08660 -0.0219 0.5951 1.0000
8.500 0.4447 0.09933 0.08898 -0.0219 0.5813 1.0000
8.750 0.4436 0.10074 0.09041 -0.0208 0.5685 1.0000
9.000 0.4489 0.10304 0.09277 -0.0205 0.5581 1.0000
9.250 0.4737 0.10675 0.09655 -0.0214 0.5481 1.0000
9.500 0.4863 0.10912 0.09898 -0.0213 0.5347 1.0000
9.750 0.4808 0.11066 0.10053 -0.0206 0.5238 1.0000
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Polar data table (+)
Polar graphs
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