MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 100,000 Max Cl/Cd: 49.63 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh42-il-100000-n5.txt Download as CSV file: xf-mh42-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5079 0.09121 0.08645 -0.0097 1.0000 0.0143
-8.750 -0.5085 0.08665 0.08195 -0.0122 1.0000 0.0141
-8.500 -0.5094 0.08223 0.07758 -0.0148 1.0000 0.0139
-8.250 -0.5135 0.07706 0.07249 -0.0183 1.0000 0.0138
-8.000 -0.5193 0.07181 0.06731 -0.0226 1.0000 0.0135
-7.750 -0.5233 0.06570 0.06120 -0.0277 1.0000 0.0133
-7.500 -0.5255 0.05937 0.05478 -0.0317 1.0000 0.0131
-7.250 -0.5249 0.05373 0.04897 -0.0341 1.0000 0.0128
-7.000 -0.5223 0.04823 0.04320 -0.0357 1.0000 0.0126
-6.750 -0.5162 0.04316 0.03775 -0.0362 1.0000 0.0125
-6.500 -0.5063 0.03875 0.03289 -0.0361 1.0000 0.0127
-6.250 -0.4931 0.03500 0.02864 -0.0354 1.0000 0.0134
-6.000 -0.4770 0.03192 0.02497 -0.0343 1.0000 0.0145
-5.750 -0.4592 0.02954 0.02210 -0.0330 1.0000 0.0152
-5.500 -0.4429 0.02687 0.01904 -0.0315 1.0000 0.0163
-5.250 -0.4261 0.02483 0.01677 -0.0300 1.0000 0.0171
-5.000 -0.4087 0.02315 0.01489 -0.0283 1.0000 0.0182
-4.750 -0.3917 0.02174 0.01331 -0.0265 1.0000 0.0195
-4.500 -0.3561 0.02005 0.01137 -0.0281 0.9893 0.0223
-4.250 -0.3203 0.01864 0.00986 -0.0300 0.9795 0.0304
-4.000 -0.2845 0.01733 0.00844 -0.0318 0.9694 0.0437
-3.750 -0.2512 0.01606 0.00727 -0.0331 0.9580 0.0791
-3.500 -0.2183 0.01508 0.00657 -0.0344 0.9464 0.1532
-3.250 -0.1865 0.01435 0.00617 -0.0356 0.9345 0.2409
-3.000 -0.1563 0.01369 0.00584 -0.0363 0.9223 0.3362
-2.750 -0.1279 0.01309 0.00558 -0.0364 0.9098 0.4408
-2.500 -0.1010 0.01258 0.00536 -0.0358 0.8974 0.5511
-2.250 -0.0750 0.01218 0.00524 -0.0347 0.8852 0.6566
-2.000 -0.0487 0.01193 0.00515 -0.0334 0.8732 0.7493
-1.750 -0.0183 0.01179 0.00506 -0.0328 0.8612 0.8281
-1.500 0.0213 0.01172 0.00492 -0.0343 0.8500 0.8912
-1.250 0.0659 0.01167 0.00470 -0.0371 0.8389 0.9380
-1.000 0.1131 0.01163 0.00447 -0.0407 0.8277 0.9722
-0.750 0.1604 0.01157 0.00423 -0.0446 0.8160 1.0000
-0.500 0.1825 0.01160 0.00410 -0.0435 0.8022 1.0000
-0.250 0.2053 0.01165 0.00402 -0.0425 0.7889 1.0000
0.000 0.2285 0.01172 0.00395 -0.0415 0.7760 1.0000
0.250 0.2518 0.01179 0.00391 -0.0406 0.7633 1.0000
0.500 0.2754 0.01188 0.00389 -0.0396 0.7504 1.0000
0.750 0.2992 0.01198 0.00390 -0.0388 0.7375 1.0000
1.000 0.3232 0.01208 0.00393 -0.0379 0.7246 1.0000
1.250 0.3474 0.01219 0.00397 -0.0371 0.7118 1.0000
1.500 0.3717 0.01231 0.00404 -0.0363 0.6988 1.0000
1.750 0.3963 0.01243 0.00411 -0.0355 0.6857 1.0000
2.000 0.4209 0.01256 0.00419 -0.0348 0.6723 1.0000
2.250 0.4458 0.01269 0.00429 -0.0340 0.6586 1.0000
2.500 0.4707 0.01283 0.00440 -0.0333 0.6446 1.0000
2.750 0.4957 0.01298 0.00457 -0.0326 0.6301 1.0000
3.000 0.5207 0.01313 0.00471 -0.0319 0.6150 1.0000
3.250 0.5457 0.01328 0.00485 -0.0312 0.5995 1.0000
3.500 0.5708 0.01345 0.00503 -0.0306 0.5825 1.0000
3.750 0.5958 0.01362 0.00527 -0.0299 0.5643 1.0000
4.000 0.6207 0.01380 0.00545 -0.0292 0.5456 1.0000
4.250 0.6455 0.01400 0.00568 -0.0285 0.5247 1.0000
4.500 0.6701 0.01422 0.00590 -0.0278 0.5032 1.0000
4.750 0.6947 0.01447 0.00622 -0.0271 0.4788 1.0000
5.000 0.7189 0.01475 0.00652 -0.0263 0.4525 1.0000
5.250 0.7427 0.01507 0.00684 -0.0256 0.4239 1.0000
5.500 0.7661 0.01546 0.00719 -0.0248 0.3924 1.0000
5.750 0.7891 0.01590 0.00761 -0.0240 0.3578 1.0000
6.000 0.8114 0.01644 0.00809 -0.0232 0.3209 1.0000
6.250 0.8330 0.01707 0.00863 -0.0223 0.2818 1.0000
6.500 0.8540 0.01780 0.00934 -0.0215 0.2428 1.0000
6.750 0.8743 0.01864 0.01007 -0.0206 0.2041 1.0000
7.000 0.8941 0.01956 0.01089 -0.0197 0.1669 1.0000
7.250 0.9131 0.02058 0.01181 -0.0188 0.1345 1.0000
7.500 0.9316 0.02167 0.01282 -0.0179 0.1058 1.0000
7.750 0.9489 0.02287 0.01394 -0.0168 0.0833 1.0000
8.000 0.9661 0.02409 0.01519 -0.0156 0.0655 1.0000
8.250 0.9813 0.02551 0.01666 -0.0142 0.0542 1.0000
8.500 0.9957 0.02696 0.01815 -0.0128 0.0446 1.0000
8.750 1.0092 0.02845 0.01981 -0.0114 0.0378 1.0000
9.000 1.0207 0.03027 0.02178 -0.0095 0.0338 1.0000
9.250 1.0335 0.03180 0.02348 -0.0080 0.0288 1.0000
9.500 1.0414 0.03386 0.02559 -0.0063 0.0252 1.0000
9.750 1.0528 0.03593 0.02794 -0.0046 0.0229 1.0000
10.000 1.0607 0.03766 0.02985 -0.0030 0.0197 1.0000
10.250 1.0627 0.03959 0.03187 -0.0010 0.0177 1.0000
10.500 1.0633 0.04258 0.03503 0.0008 0.0165 1.0000
10.750 1.0653 0.04541 0.03820 0.0024 0.0156 1.0000
11.000 1.0639 0.04854 0.04163 0.0037 0.0151 1.0000
11.250 1.0589 0.05194 0.04533 0.0045 0.0144 1.0000
11.500 1.0517 0.05554 0.04919 0.0046 0.0140 1.0000
11.750 1.0417 0.05966 0.05357 0.0041 0.0137 1.0000
12.000 1.0305 0.06405 0.05819 0.0027 0.0132 1.0000
12.250 1.0159 0.06941 0.06380 0.0005 0.0133 1.0000
12.500 1.0005 0.07522 0.06982 -0.0025 0.0132 1.0000
12.750 0.9812 0.08233 0.07713 -0.0066 0.0135 1.0000
13.000 0.9620 0.09001 0.08499 -0.0116 0.0135 1.0000
13.250 0.9386 0.09945 0.09460 -0.0177 0.0141 1.0000
13.500 0.9191 0.10882 0.10407 -0.0236 0.0149 1.0000
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Polar data table (+)
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