MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 100,000 Max Cl/Cd: 46.34 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh46-il-100000-n5.txt Download as CSV file: xf-mh46-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5651 0.08044 0.07577 -0.0104 1.0000 0.0133
-8.750 -0.5708 0.07433 0.06972 -0.0144 1.0000 0.0132
-8.500 -0.5783 0.06735 0.06276 -0.0205 1.0000 0.0130
-8.250 -0.5909 0.06150 0.05684 -0.0247 1.0000 0.0129
-8.000 -0.5979 0.05645 0.05163 -0.0270 1.0000 0.0127
-7.750 -0.6027 0.05124 0.04616 -0.0284 1.0000 0.0126
-7.500 -0.6020 0.04654 0.04112 -0.0289 1.0000 0.0125
-7.250 -0.5967 0.04219 0.03637 -0.0287 1.0000 0.0125
-7.000 -0.5876 0.03817 0.03187 -0.0280 1.0000 0.0126
-6.750 -0.5744 0.03478 0.02799 -0.0270 1.0000 0.0127
-6.500 -0.5576 0.03209 0.02479 -0.0259 1.0000 0.0134
-6.250 -0.5422 0.02927 0.02169 -0.0250 1.0000 0.0146
-6.000 -0.5228 0.02766 0.01986 -0.0241 1.0000 0.0162
-5.750 -0.5025 0.02581 0.01772 -0.0230 1.0000 0.0176
-5.500 -0.4821 0.02391 0.01554 -0.0216 1.0000 0.0186
-5.250 -0.4624 0.02228 0.01370 -0.0200 1.0000 0.0198
-5.000 -0.4440 0.02100 0.01224 -0.0182 1.0000 0.0211
-4.750 -0.4292 0.01967 0.01083 -0.0162 1.0000 0.0243
-4.500 -0.4130 0.01889 0.00994 -0.0142 1.0000 0.0304
-4.250 -0.3819 0.01752 0.00851 -0.0152 0.9895 0.0440
-4.000 -0.3475 0.01617 0.00743 -0.0170 0.9791 0.0915
-3.750 -0.3124 0.01517 0.00678 -0.0190 0.9691 0.1710
-3.500 -0.2792 0.01448 0.00638 -0.0205 0.9576 0.2547
-3.250 -0.2467 0.01393 0.00602 -0.0216 0.9460 0.3341
-3.000 -0.2152 0.01348 0.00576 -0.0224 0.9342 0.4077
-2.750 -0.1848 0.01309 0.00554 -0.0228 0.9224 0.4791
-2.500 -0.1554 0.01274 0.00534 -0.0227 0.9106 0.5497
-2.250 -0.1266 0.01240 0.00518 -0.0224 0.8989 0.6230
-2.000 -0.0980 0.01208 0.00502 -0.0219 0.8871 0.7023
-1.750 -0.0640 0.01181 0.00494 -0.0221 0.8757 0.7922
-1.500 -0.0117 0.01167 0.00483 -0.0261 0.8661 0.8790
-1.250 0.0400 0.01164 0.00464 -0.0304 0.8556 0.9340
-1.000 0.0852 0.01164 0.00448 -0.0336 0.8435 0.9701
-0.750 0.1300 0.01162 0.00430 -0.0370 0.8308 0.9989
-0.500 0.1534 0.01164 0.00417 -0.0361 0.8158 1.0000
-0.250 0.1758 0.01168 0.00408 -0.0349 0.8010 1.0000
0.000 0.1985 0.01173 0.00402 -0.0338 0.7864 1.0000
0.250 0.2217 0.01179 0.00398 -0.0327 0.7718 1.0000
0.500 0.2452 0.01185 0.00395 -0.0317 0.7573 1.0000
0.750 0.2687 0.01193 0.00393 -0.0307 0.7425 1.0000
1.000 0.2924 0.01201 0.00394 -0.0297 0.7275 1.0000
1.250 0.3163 0.01210 0.00395 -0.0288 0.7123 1.0000
1.500 0.3403 0.01219 0.00400 -0.0278 0.6967 1.0000
1.750 0.3644 0.01229 0.00403 -0.0269 0.6809 1.0000
2.000 0.3886 0.01240 0.00408 -0.0259 0.6646 1.0000
2.250 0.4130 0.01252 0.00417 -0.0251 0.6467 1.0000
2.500 0.4374 0.01264 0.00426 -0.0242 0.6287 1.0000
2.750 0.4617 0.01278 0.00438 -0.0233 0.6106 1.0000
3.000 0.4862 0.01294 0.00452 -0.0225 0.5908 1.0000
3.250 0.5106 0.01310 0.00466 -0.0217 0.5709 1.0000
3.500 0.5351 0.01329 0.00486 -0.0209 0.5502 1.0000
3.750 0.5595 0.01350 0.00504 -0.0201 0.5289 1.0000
4.000 0.5839 0.01373 0.00526 -0.0193 0.5066 1.0000
4.250 0.6080 0.01399 0.00549 -0.0185 0.4841 1.0000
4.500 0.6322 0.01427 0.00576 -0.0177 0.4601 1.0000
4.750 0.6562 0.01458 0.00611 -0.0169 0.4353 1.0000
5.000 0.6800 0.01492 0.00644 -0.0162 0.4095 1.0000
5.250 0.7036 0.01530 0.00681 -0.0154 0.3825 1.0000
5.500 0.7268 0.01572 0.00721 -0.0146 0.3542 1.0000
5.750 0.7497 0.01618 0.00765 -0.0138 0.3244 1.0000
6.000 0.7722 0.01670 0.00819 -0.0130 0.2934 1.0000
6.250 0.7943 0.01728 0.00874 -0.0122 0.2607 1.0000
6.500 0.8157 0.01795 0.00935 -0.0114 0.2268 1.0000
6.750 0.8366 0.01870 0.01003 -0.0105 0.1929 1.0000
7.000 0.8568 0.01955 0.01080 -0.0097 0.1598 1.0000
7.250 0.8762 0.02051 0.01167 -0.0087 0.1293 1.0000
7.500 0.8949 0.02156 0.01265 -0.0078 0.1008 1.0000
7.750 0.9124 0.02275 0.01378 -0.0067 0.0791 1.0000
8.000 0.9290 0.02405 0.01513 -0.0054 0.0627 1.0000
8.250 0.9444 0.02542 0.01652 -0.0041 0.0514 1.0000
8.500 0.9595 0.02681 0.01805 -0.0026 0.0443 1.0000
8.750 0.9725 0.02840 0.01974 -0.0010 0.0387 1.0000
9.000 0.9867 0.02976 0.02124 0.0004 0.0334 1.0000
9.250 0.9950 0.03185 0.02334 0.0023 0.0305 1.0000
9.500 1.0083 0.03365 0.02541 0.0040 0.0283 1.0000
9.750 1.0198 0.03542 0.02740 0.0055 0.0253 1.0000
10.000 1.0278 0.03708 0.02916 0.0070 0.0227 1.0000
10.250 1.0315 0.03980 0.03199 0.0089 0.0211 1.0000
10.500 1.0358 0.04235 0.03483 0.0109 0.0201 1.0000
10.750 1.0365 0.04494 0.03773 0.0128 0.0191 1.0000
11.000 1.0339 0.04749 0.04062 0.0142 0.0178 1.0000
11.250 1.0291 0.05046 0.04385 0.0151 0.0170 1.0000
11.500 1.0230 0.05347 0.04707 0.0152 0.0161 1.0000
11.750 1.0153 0.05690 0.05068 0.0147 0.0154 1.0000
12.000 1.0057 0.06098 0.05497 0.0136 0.0151 1.0000
12.250 0.9934 0.06572 0.05989 0.0117 0.0148 1.0000
12.500 0.9789 0.07128 0.06567 0.0090 0.0148 1.0000
12.750 0.9625 0.07760 0.07219 0.0053 0.0149 1.0000
13.000 0.9423 0.08522 0.08001 0.0005 0.0149 1.0000
13.250 0.9123 0.09603 0.09106 -0.0064 0.0160 1.0000
13.500 0.8758 0.10974 0.10486 -0.0148 0.0179 1.0000
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Polar data table (+)
Polar graphs
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