MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 50,000 Max Cl/Cd: 29.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh95-il-50000.txt Download as CSV file: xf-mh95-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5438 0.09461 0.08729 -0.0526 1.0000 0.1380
-10.500 -0.5142 0.09402 0.08676 -0.0487 1.0000 0.1413
-10.250 -0.5540 0.08536 0.07813 -0.0521 1.0000 0.1323
-10.000 -0.6773 0.07760 0.07021 -0.0499 1.0000 0.1230
-9.750 -0.6929 0.07445 0.06705 -0.0466 1.0000 0.1217
-9.500 -0.7154 0.07142 0.06399 -0.0425 1.0000 0.1204
-9.250 -0.7386 0.06822 0.06068 -0.0383 1.0000 0.1187
-9.000 -0.7621 0.06496 0.05723 -0.0338 1.0000 0.1172
-8.750 -0.7830 0.06162 0.05362 -0.0292 1.0000 0.1155
-8.500 -0.7987 0.05835 0.05000 -0.0248 1.0000 0.1140
-8.250 -0.8064 0.05535 0.04667 -0.0209 1.0000 0.1136
-8.000 -0.8076 0.05260 0.04360 -0.0176 1.0000 0.1137
-7.750 -0.8037 0.05006 0.04080 -0.0147 1.0000 0.1146
-7.500 -0.7972 0.04757 0.03802 -0.0119 1.0000 0.1154
-7.250 -0.7876 0.04519 0.03534 -0.0094 1.0000 0.1164
-7.000 -0.7748 0.04294 0.03279 -0.0072 1.0000 0.1175
-6.750 -0.7591 0.04087 0.03042 -0.0052 1.0000 0.1194
-6.500 -0.7418 0.03905 0.02824 -0.0032 1.0000 0.1224
-6.250 -0.7213 0.03728 0.02647 -0.0019 1.0000 0.1278
-6.000 -0.7007 0.03589 0.02500 -0.0005 1.0000 0.1354
-5.750 -0.6764 0.03439 0.02360 0.0006 1.0000 0.1446
-5.500 -0.6536 0.03310 0.02241 0.0020 1.0000 0.1587
-5.250 -0.6343 0.03179 0.02125 0.0038 1.0000 0.1840
-5.000 -0.6227 0.03004 0.02008 0.0066 1.0000 0.2300
-4.750 -0.6302 0.02710 0.01867 0.0121 1.0000 0.3691
-4.500 -0.6361 0.02652 0.01966 0.0210 1.0000 0.5752
-4.250 -0.6291 0.02802 0.02131 0.0281 1.0000 0.6618
-4.000 -0.6168 0.03009 0.02332 0.0349 1.0000 0.7138
-3.750 -0.5874 0.03348 0.02657 0.0409 1.0000 0.7587
-3.500 -0.5373 0.03710 0.02989 0.0435 1.0000 0.8054
-3.250 -0.4476 0.03970 0.03201 0.0370 1.0000 0.8428
-3.000 -0.3459 0.04077 0.03262 0.0256 1.0000 0.8726
-2.750 -0.2858 0.04083 0.03239 0.0196 1.0000 0.9011
-2.500 -0.2336 0.04069 0.03202 0.0141 1.0000 0.9288
-2.250 -0.1620 0.04027 0.03136 0.0046 1.0000 0.9545
-2.000 -0.0919 0.03973 0.03059 -0.0053 1.0000 0.9793
-1.750 -0.0211 0.03915 0.02980 -0.0160 1.0000 1.0000
-1.500 -0.0240 0.03904 0.02967 -0.0135 1.0000 1.0000
-1.250 -0.0269 0.03900 0.02960 -0.0111 1.0000 1.0000
-1.000 -0.0296 0.03902 0.02960 -0.0086 1.0000 1.0000
-0.750 -0.0323 0.03909 0.02965 -0.0061 1.0000 1.0000
-0.500 -0.0349 0.03922 0.02975 -0.0037 1.0000 1.0000
-0.250 -0.0375 0.03939 0.02991 -0.0013 1.0000 1.0000
0.000 -0.0343 0.03962 0.03012 0.0001 0.9986 1.0000
0.250 0.0359 0.04037 0.03080 -0.0105 0.9762 1.0000
0.500 0.0945 0.04094 0.03132 -0.0184 0.9557 1.0000
0.750 0.1384 0.04118 0.03153 -0.0233 0.9342 1.0000
1.000 0.1831 0.04136 0.03170 -0.0279 0.9132 1.0000
1.250 0.2321 0.04142 0.03175 -0.0329 0.8932 1.0000
1.500 0.2805 0.04131 0.03164 -0.0373 0.8733 1.0000
1.750 0.3085 0.04123 0.03157 -0.0382 0.8513 1.0000
2.000 0.3470 0.04098 0.03134 -0.0405 0.8306 1.0000
2.250 0.3913 0.04050 0.03090 -0.0432 0.8106 1.0000
2.500 0.4412 0.03973 0.03018 -0.0464 0.7912 1.0000
2.750 0.4954 0.03863 0.02915 -0.0498 0.7726 1.0000
3.000 0.5626 0.03692 0.02752 -0.0546 0.7544 1.0000
3.250 0.6374 0.03477 0.02546 -0.0602 0.7354 1.0000
3.500 0.6657 0.03407 0.02480 -0.0592 0.7109 1.0000
3.750 0.7222 0.03235 0.02311 -0.0618 0.6865 1.0000
4.000 0.7717 0.03096 0.02169 -0.0635 0.6596 1.0000
4.250 0.8048 0.03026 0.02092 -0.0629 0.6309 1.0000
4.500 0.8283 0.03004 0.02062 -0.0611 0.6027 1.0000
4.750 0.8598 0.02961 0.02001 -0.0605 0.5740 1.0000
5.000 0.8693 0.02999 0.02034 -0.0570 0.5475 1.0000
5.250 0.8916 0.03003 0.02022 -0.0552 0.5213 1.0000
5.500 0.9034 0.03047 0.02057 -0.0522 0.4971 1.0000
5.750 0.9142 0.03098 0.02101 -0.0490 0.4739 1.0000
6.000 0.9292 0.03144 0.02134 -0.0465 0.4515 1.0000
6.500 0.9558 0.03268 0.02234 -0.0412 0.4105 1.0000
6.750 0.9649 0.03347 0.02307 -0.0380 0.3923 1.0000
7.000 0.9755 0.03429 0.02381 -0.0350 0.3751 1.0000
7.250 0.9872 0.03516 0.02461 -0.0323 0.3589 1.0000
7.500 0.9828 0.03627 0.02588 -0.0272 0.3461 1.0000
7.750 0.9861 0.03738 0.02701 -0.0234 0.3338 1.0000
8.000 1.0006 0.03838 0.02791 -0.0212 0.3214 1.0000
8.250 0.9938 0.03966 0.02936 -0.0160 0.3124 1.0000
8.500 1.0033 0.04095 0.03062 -0.0132 0.3030 1.0000
8.750 0.9962 0.04238 0.03221 -0.0081 0.2955 1.0000
9.000 1.0110 0.04371 0.03347 -0.0063 0.2867 1.0000
9.250 0.9942 0.04570 0.03572 -0.0005 0.2815 1.0000
9.500 1.0144 0.04715 0.03713 0.0004 0.2737 1.0000
9.750 1.0065 0.04956 0.03970 0.0044 0.2693 1.0000
10.000 0.9776 0.05256 0.04298 0.0104 0.2665 1.0000
10.250 0.9423 0.05593 0.04656 0.0164 0.2645 1.0000
10.500 0.8851 0.06112 0.05193 0.0222 0.2646 1.0000
10.750 0.7714 0.07378 0.06470 0.0238 0.2690 1.0000
11.000 0.6887 0.08981 0.08073 0.0177 0.2719 1.0000
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Polar data table (+)
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