MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 500,000 Max Cl/Cd: 78.54 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh42-il-500000-n5.txt Download as CSV file: xf-mh42-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 42 8.94%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5217 0.08522 0.08306 -0.0092 1.0000 0.0041
-8.750 -0.5257 0.08021 0.07809 -0.0120 1.0000 0.0040
-8.500 -0.5302 0.07533 0.07325 -0.0150 1.0000 0.0039
-8.250 -0.5416 0.06953 0.06751 -0.0192 1.0000 0.0038
-8.000 -0.5524 0.06259 0.06056 -0.0261 1.0000 0.0038
-7.750 -0.5583 0.05413 0.05198 -0.0319 1.0000 0.0037
-7.500 -0.5654 0.04427 0.04183 -0.0352 1.0000 0.0034
-7.250 -0.5888 0.02799 0.02442 -0.0346 1.0000 0.0028
-7.000 -0.5694 0.02391 0.01978 -0.0348 0.9841 0.0028
-6.750 -0.5414 0.02110 0.01651 -0.0359 0.9643 0.0027
-6.500 -0.5147 0.01902 0.01405 -0.0362 0.9455 0.0027
-6.250 -0.4913 0.01734 0.01205 -0.0355 0.9268 0.0027
-6.000 -0.4690 0.01599 0.01041 -0.0345 0.9088 0.0027
-5.750 -0.4462 0.01492 0.00911 -0.0334 0.8921 0.0027
-5.500 -0.4232 0.01388 0.00783 -0.0324 0.8765 0.0028
-5.250 -0.3993 0.01305 0.00682 -0.0316 0.8617 0.0029
-5.000 -0.3749 0.01232 0.00592 -0.0308 0.8473 0.0030
-4.750 -0.3497 0.01176 0.00521 -0.0302 0.8335 0.0031
-4.500 -0.3239 0.01129 0.00461 -0.0297 0.8201 0.0034
-4.250 -0.2978 0.01088 0.00406 -0.0292 0.8071 0.0038
-4.000 -0.2713 0.01055 0.00361 -0.0289 0.7946 0.0044
-3.750 -0.2447 0.01019 0.00312 -0.0284 0.7824 0.0063
-3.500 -0.2181 0.00988 0.00279 -0.0281 0.7705 0.0147
-3.250 -0.1918 0.00952 0.00250 -0.0279 0.7590 0.0365
-3.000 -0.1662 0.00901 0.00223 -0.0276 0.7478 0.0968
-2.750 -0.1393 0.00878 0.00204 -0.0274 0.7366 0.1281
-2.500 -0.1122 0.00859 0.00188 -0.0273 0.7255 0.1563
-2.250 -0.0852 0.00838 0.00172 -0.0271 0.7149 0.1929
-2.000 -0.0588 0.00807 0.00159 -0.0269 0.7044 0.2563
-1.750 -0.0322 0.00781 0.00147 -0.0268 0.6940 0.3152
-1.500 -0.0056 0.00757 0.00138 -0.0266 0.6836 0.3758
-1.250 0.0210 0.00733 0.00129 -0.0264 0.6733 0.4428
-1.000 0.0474 0.00711 0.00123 -0.0261 0.6632 0.5071
-0.750 0.0736 0.00691 0.00118 -0.0258 0.6528 0.5700
-0.500 0.0997 0.00672 0.00115 -0.0254 0.6422 0.6337
-0.250 0.1255 0.00655 0.00113 -0.0248 0.6317 0.6948
0.000 0.1511 0.00641 0.00114 -0.0242 0.6211 0.7517
0.250 0.1765 0.00629 0.00115 -0.0235 0.6103 0.8044
0.500 0.2018 0.00620 0.00116 -0.0227 0.5991 0.8558
0.750 0.2298 0.00615 0.00119 -0.0224 0.5873 0.9068
1.000 0.2680 0.00618 0.00122 -0.0244 0.5741 0.9474
1.250 0.3091 0.00624 0.00123 -0.0272 0.5599 0.9723
1.500 0.3480 0.00633 0.00125 -0.0297 0.5450 0.9880
1.750 0.3851 0.00642 0.00128 -0.0317 0.5291 0.9990
2.000 0.4125 0.00652 0.00131 -0.0317 0.5138 1.0000
2.250 0.4381 0.00663 0.00136 -0.0312 0.4974 1.0000
2.500 0.4637 0.00676 0.00143 -0.0308 0.4799 1.0000
2.750 0.4893 0.00691 0.00152 -0.0303 0.4615 1.0000
3.000 0.5149 0.00707 0.00161 -0.0299 0.4415 1.0000
3.250 0.5405 0.00725 0.00172 -0.0295 0.4205 1.0000
3.500 0.5661 0.00744 0.00184 -0.0291 0.3981 1.0000
3.750 0.5916 0.00767 0.00200 -0.0287 0.3740 1.0000
4.000 0.6170 0.00792 0.00216 -0.0283 0.3481 1.0000
4.250 0.6424 0.00819 0.00234 -0.0280 0.3208 1.0000
4.500 0.6676 0.00850 0.00255 -0.0276 0.2918 1.0000
4.750 0.6926 0.00884 0.00280 -0.0272 0.2622 1.0000
5.000 0.7177 0.00919 0.00305 -0.0269 0.2339 1.0000
5.250 0.7426 0.00955 0.00332 -0.0265 0.2067 1.0000
5.500 0.7671 0.00998 0.00363 -0.0261 0.1771 1.0000
6.000 0.8154 0.01094 0.00434 -0.0253 0.1178 1.0000
6.250 0.8396 0.01140 0.00475 -0.0248 0.0967 1.0000
6.500 0.8639 0.01184 0.00514 -0.0244 0.0790 1.0000
6.750 0.8876 0.01235 0.00557 -0.0240 0.0610 1.0000
7.000 0.9114 0.01284 0.00602 -0.0235 0.0480 1.0000
7.250 0.9352 0.01332 0.00649 -0.0230 0.0380 1.0000
7.500 0.9587 0.01382 0.00700 -0.0225 0.0294 1.0000
7.750 0.9818 0.01437 0.00755 -0.0219 0.0221 1.0000
8.000 1.0042 0.01498 0.00814 -0.0213 0.0157 1.0000
8.250 1.0265 0.01558 0.00877 -0.0207 0.0117 1.0000
8.500 1.0488 0.01616 0.00942 -0.0200 0.0094 1.0000
8.750 1.0708 0.01675 0.01007 -0.0193 0.0072 1.0000
9.000 1.0911 0.01753 0.01090 -0.0185 0.0053 1.0000
9.250 1.1113 0.01829 0.01174 -0.0176 0.0039 1.0000
9.500 1.1292 0.01928 0.01283 -0.0164 0.0031 1.0000
9.750 1.1466 0.02027 0.01394 -0.0152 0.0028 1.0000
10.000 1.1637 0.02120 0.01500 -0.0140 0.0026 1.0000
10.250 1.1806 0.02207 0.01597 -0.0128 0.0023 1.0000
10.500 1.1969 0.02292 0.01695 -0.0116 0.0020 1.0000
10.750 1.2112 0.02390 0.01803 -0.0102 0.0019 1.0000
11.000 1.2239 0.02491 0.01913 -0.0087 0.0016 1.0000
11.250 1.2285 0.02624 0.02059 -0.0060 0.0015 1.0000
11.500 1.2297 0.02773 0.02223 -0.0033 0.0015 1.0000
11.750 1.2282 0.02957 0.02423 -0.0009 0.0014 1.0000
12.000 1.2284 0.03148 0.02628 0.0008 0.0014 1.0000
12.250 1.2304 0.03338 0.02833 0.0019 0.0014 1.0000
12.500 1.2309 0.03562 0.03072 0.0027 0.0013 1.0000
12.750 1.2275 0.03841 0.03368 0.0031 0.0013 1.0000
13.000 1.2238 0.04148 0.03691 0.0030 0.0013 1.0000
13.250 1.2196 0.04481 0.04040 0.0025 0.0012 1.0000
13.500 1.2133 0.04860 0.04435 0.0015 0.0013 1.0000
13.750 1.2084 0.05246 0.04836 0.0002 0.0012 1.0000
14.000 1.1966 0.05750 0.05357 -0.0018 0.0012 1.0000
14.250 1.1858 0.06274 0.05898 -0.0042 0.0012 1.0000
14.500 1.1688 0.06925 0.06565 -0.0075 0.0013 1.0000
14.750 1.1584 0.07506 0.07161 -0.0106 0.0012 1.0000
15.000 1.1426 0.08216 0.07886 -0.0144 0.0012 1.0000
15.250 1.1287 0.08933 0.08618 -0.0184 0.0012 1.0000
15.500 1.1046 0.09888 0.09588 -0.0238 0.0012 1.0000
15.750 1.0857 0.10774 0.10487 -0.0286 0.0013 1.0000
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Polar data table (+)
Polar graphs
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