MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.24 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh42-il-1000000-n5.txt Download as CSV file: xf-mh42-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5380 0.07604 0.07454 -0.0136 1.0000 0.0024
-8.500 -0.5453 0.07094 0.06947 -0.0170 1.0000 0.0024
-8.250 -0.5651 0.06390 0.06246 -0.0235 1.0000 0.0024
-8.000 -0.5750 0.05463 0.05309 -0.0307 1.0000 0.0024
-7.750 -0.5848 0.04368 0.04189 -0.0350 0.9878 0.0023
-7.500 -0.5923 0.02986 0.02726 -0.0378 0.9332 0.0021
-7.250 -0.5876 0.02447 0.02125 -0.0358 0.9056 0.0021
-7.000 -0.5745 0.02077 0.01700 -0.0341 0.8858 0.0020
-6.750 -0.5561 0.01815 0.01393 -0.0328 0.8689 0.0019
-6.500 -0.5349 0.01622 0.01163 -0.0318 0.8532 0.0019
-6.250 -0.5121 0.01472 0.00982 -0.0309 0.8383 0.0019
-6.000 -0.4883 0.01353 0.00838 -0.0301 0.8242 0.0019
-5.750 -0.4635 0.01263 0.00727 -0.0295 0.8104 0.0019
-5.500 -0.4384 0.01182 0.00626 -0.0289 0.7972 0.0019
-5.250 -0.4128 0.01116 0.00544 -0.0285 0.7845 0.0019
-5.000 -0.3868 0.01059 0.00472 -0.0280 0.7723 0.0019
-4.750 -0.3604 0.01013 0.00413 -0.0277 0.7606 0.0019
-4.500 -0.3337 0.00973 0.00362 -0.0274 0.7490 0.0020
-4.250 -0.3068 0.00938 0.00316 -0.0271 0.7375 0.0021
-4.000 -0.2796 0.00912 0.00281 -0.0269 0.7266 0.0022
-3.750 -0.2522 0.00889 0.00247 -0.0267 0.7160 0.0024
-3.500 -0.2248 0.00867 0.00217 -0.0265 0.7057 0.0031
-3.000 -0.1699 0.00826 0.00174 -0.0263 0.6850 0.0149
-2.750 -0.1427 0.00804 0.00156 -0.0261 0.6751 0.0314
-2.500 -0.1155 0.00779 0.00139 -0.0260 0.6653 0.0617
-2.250 -0.0887 0.00748 0.00123 -0.0259 0.6554 0.1135
-2.000 -0.0614 0.00727 0.00113 -0.0259 0.6457 0.1519
-1.750 -0.0339 0.00711 0.00103 -0.0258 0.6359 0.1853
-1.500 -0.0067 0.00692 0.00095 -0.0257 0.6259 0.2307
-1.250 0.0206 0.00671 0.00087 -0.0257 0.6156 0.2835
-1.000 0.0479 0.00655 0.00082 -0.0256 0.6054 0.3323
-0.750 0.0751 0.00638 0.00077 -0.0255 0.5949 0.3857
-0.500 0.1024 0.00625 0.00074 -0.0255 0.5839 0.4339
-0.250 0.1297 0.00611 0.00071 -0.0254 0.5725 0.4849
0.000 0.1569 0.00599 0.00070 -0.0253 0.5611 0.5348
0.250 0.1839 0.00587 0.00069 -0.0251 0.5494 0.5883
0.500 0.2108 0.00576 0.00070 -0.0249 0.5369 0.6424
0.750 0.2375 0.00566 0.00072 -0.0247 0.5241 0.6943
1.000 0.2639 0.00558 0.00075 -0.0243 0.5103 0.7454
1.250 0.2898 0.00550 0.00079 -0.0238 0.4963 0.7978
1.500 0.3151 0.00542 0.00084 -0.0232 0.4816 0.8504
1.750 0.3403 0.00538 0.00090 -0.0224 0.4657 0.9030
2.000 0.3725 0.00542 0.00097 -0.0232 0.4476 0.9514
2.250 0.4141 0.00555 0.00103 -0.0263 0.4257 0.9769
2.500 0.4510 0.00570 0.00110 -0.0284 0.4041 0.9892
3.000 0.5159 0.00605 0.00128 -0.0306 0.3570 1.0000
3.250 0.5414 0.00625 0.00139 -0.0302 0.3346 1.0000
3.500 0.5669 0.00647 0.00151 -0.0298 0.3100 1.0000
3.750 0.5923 0.00670 0.00165 -0.0294 0.2855 1.0000
4.000 0.6177 0.00695 0.00180 -0.0290 0.2592 1.0000
4.250 0.6429 0.00723 0.00197 -0.0286 0.2325 1.0000
4.500 0.6684 0.00749 0.00215 -0.0282 0.2091 1.0000
4.750 0.6938 0.00778 0.00236 -0.0279 0.1864 1.0000
5.000 0.7189 0.00811 0.00258 -0.0275 0.1608 1.0000
5.250 0.7443 0.00840 0.00281 -0.0272 0.1408 1.0000
5.500 0.7687 0.00885 0.00310 -0.0267 0.1095 1.0000
5.750 0.7939 0.00918 0.00336 -0.0264 0.0915 1.0000
6.000 0.8187 0.00958 0.00366 -0.0260 0.0720 1.0000
6.250 0.8438 0.00992 0.00398 -0.0257 0.0588 1.0000
6.500 0.8688 0.01027 0.00428 -0.0253 0.0477 1.0000
6.750 0.8938 0.01062 0.00461 -0.0250 0.0385 1.0000
7.000 0.9182 0.01105 0.00498 -0.0245 0.0275 1.0000
7.250 0.9421 0.01153 0.00540 -0.0241 0.0172 1.0000
7.500 0.9667 0.01191 0.00578 -0.0237 0.0136 1.0000
7.750 0.9909 0.01232 0.00620 -0.0233 0.0104 1.0000
8.000 1.0155 0.01268 0.00659 -0.0229 0.0089 1.0000
8.250 1.0390 0.01316 0.00709 -0.0224 0.0063 1.0000
8.500 1.0624 0.01363 0.00758 -0.0219 0.0042 1.0000
8.750 1.0850 0.01420 0.00815 -0.0212 0.0024 1.0000
9.000 1.1074 0.01477 0.00876 -0.0206 0.0016 1.0000
9.250 1.1296 0.01534 0.00940 -0.0199 0.0013 1.0000
9.500 1.1517 0.01589 0.01001 -0.0193 0.0012 1.0000
9.750 1.1734 0.01645 0.01064 -0.0186 0.0011 1.0000
10.000 1.1942 0.01711 0.01137 -0.0177 0.0010 1.0000
10.250 1.2145 0.01775 0.01212 -0.0169 0.0010 1.0000
10.500 1.2342 0.01844 0.01288 -0.0160 0.0009 1.0000
10.750 1.2526 0.01920 0.01374 -0.0149 0.0009 1.0000
11.000 1.2705 0.01996 0.01457 -0.0138 0.0008 1.0000
11.250 1.2870 0.02080 0.01550 -0.0126 0.0008 1.0000
11.500 1.3019 0.02169 0.01649 -0.0112 0.0007 1.0000
11.750 1.3152 0.02263 0.01752 -0.0096 0.0007 1.0000
12.000 1.3237 0.02368 0.01868 -0.0073 0.0007 1.0000
12.250 1.3280 0.02477 0.01988 -0.0045 0.0006 1.0000
12.500 1.3292 0.02617 0.02141 -0.0019 0.0006 1.0000
12.750 1.3314 0.02767 0.02302 0.0002 0.0006 1.0000
13.000 1.3256 0.02999 0.02552 0.0022 0.0005 1.0000
13.250 1.3209 0.03249 0.02818 0.0034 0.0005 1.0000
13.500 1.3185 0.03500 0.03085 0.0041 0.0005 1.0000
13.750 1.3255 0.03671 0.03263 0.0043 0.0005 1.0000
14.000 1.3183 0.04013 0.03621 0.0041 0.0005 1.0000
14.250 1.3201 0.04269 0.03886 0.0037 0.0005 1.0000
14.500 1.3003 0.04821 0.04460 0.0022 0.0005 1.0000
14.750 1.3045 0.05079 0.04724 0.0013 0.0005 1.0000
15.000 1.2982 0.05495 0.05152 -0.0003 0.0005 1.0000
15.250 1.2988 0.05823 0.05489 -0.0016 0.0004 1.0000
15.500 1.2692 0.06656 0.06343 -0.0058 0.0005 1.0000
15.750 1.2461 0.07445 0.07149 -0.0099 0.0005 1.0000
16.000 1.2347 0.08062 0.07776 -0.0132 0.0005 1.0000
16.250 1.2178 0.08811 0.08538 -0.0173 0.0005 1.0000
16.500 1.1890 0.09839 0.09583 -0.0230 0.0005 1.0000
16.750 1.1584 0.10959 0.10717 -0.0291 0.0005 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 42 8.94% (mh42-il)