MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 50,000 Max Cl/Cd: 32.9 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh25-il-50000-n5.txt Download as CSV file: xf-mh25-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 25 9.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4768 0.09996 0.09299 -0.0380 1.0000 0.0385
-9.250 -0.4824 0.09629 0.08939 -0.0386 1.0000 0.0375
-9.000 -0.4906 0.09237 0.08556 -0.0395 1.0000 0.0367
-8.750 -0.5014 0.08836 0.08161 -0.0407 1.0000 0.0358
-8.500 -0.5172 0.08446 0.07778 -0.0410 1.0000 0.0352
-8.250 -0.5349 0.08144 0.07481 -0.0394 1.0000 0.0345
-8.000 -0.5534 0.07838 0.07176 -0.0370 1.0000 0.0340
-7.750 -0.5712 0.07454 0.06787 -0.0349 1.0000 0.0327
-7.500 -0.5870 0.07067 0.06385 -0.0323 1.0000 0.0318
-7.000 -0.6012 0.06457 0.05718 -0.0264 1.0000 0.0303
-6.750 -0.6029 0.06125 0.05374 -0.0237 1.0000 0.0300
-6.500 -0.6039 0.05790 0.05017 -0.0209 1.0000 0.0298
-6.250 -0.6023 0.05468 0.04672 -0.0181 1.0000 0.0295
-6.000 -0.5985 0.05153 0.04328 -0.0154 1.0000 0.0293
-5.750 -0.5928 0.04832 0.03971 -0.0125 1.0000 0.0292
-5.500 -0.5842 0.04532 0.03634 -0.0099 1.0000 0.0291
-5.250 -0.5730 0.04244 0.03302 -0.0073 1.0000 0.0291
-5.000 -0.5591 0.03980 0.02994 -0.0050 1.0000 0.0292
-4.750 -0.5424 0.03723 0.02688 -0.0028 1.0000 0.0295
-4.500 -0.5229 0.03496 0.02412 -0.0008 1.0000 0.0301
-4.250 -0.5025 0.03255 0.02145 0.0007 1.0000 0.0315
-4.000 -0.4822 0.03097 0.01971 0.0019 1.0000 0.0354
-3.750 -0.4587 0.02956 0.01796 0.0033 1.0000 0.0411
-3.500 -0.4342 0.02797 0.01611 0.0045 1.0000 0.0450
-3.250 -0.4101 0.02674 0.01469 0.0056 1.0000 0.0563
-3.000 -0.3870 0.02549 0.01342 0.0066 1.0000 0.0753
-2.750 -0.3099 0.02122 0.01323 0.0000 1.0000 0.8436
-2.500 -0.1432 0.02278 0.01322 -0.0249 1.0000 1.0000
-2.250 -0.1325 0.02264 0.01282 -0.0223 1.0000 1.0000
-2.000 -0.1216 0.02254 0.01249 -0.0199 1.0000 1.0000
-1.750 -0.1103 0.02247 0.01221 -0.0174 1.0000 1.0000
-1.500 -0.0988 0.02244 0.01199 -0.0150 1.0000 1.0000
-1.250 -0.0871 0.02243 0.01180 -0.0126 1.0000 1.0000
-1.000 -0.0753 0.02245 0.01166 -0.0102 1.0000 1.0000
-0.750 -0.0634 0.02250 0.01153 -0.0079 1.0000 1.0000
-0.500 -0.0515 0.02258 0.01148 -0.0056 1.0000 1.0000
-0.250 -0.0394 0.02269 0.01147 -0.0033 1.0000 1.0000
0.000 -0.0274 0.02283 0.01151 -0.0011 1.0000 1.0000
0.250 -0.0019 0.02311 0.01168 -0.0017 0.9960 1.0000
0.500 0.0369 0.02353 0.01198 -0.0048 0.9871 1.0000
0.750 0.0754 0.02397 0.01234 -0.0079 0.9780 1.0000
1.000 0.1153 0.02443 0.01276 -0.0111 0.9690 1.0000
1.250 0.1519 0.02477 0.01308 -0.0136 0.9583 1.0000
1.500 0.1877 0.02507 0.01339 -0.0159 0.9470 1.0000
1.750 0.2236 0.02533 0.01368 -0.0181 0.9353 1.0000
2.000 0.2594 0.02554 0.01396 -0.0202 0.9229 1.0000
2.250 0.2946 0.02570 0.01421 -0.0221 0.9098 1.0000
2.500 0.3288 0.02577 0.01438 -0.0236 0.8958 1.0000
2.750 0.3626 0.02577 0.01449 -0.0249 0.8809 1.0000
3.000 0.3970 0.02569 0.01454 -0.0261 0.8654 1.0000
3.250 0.4303 0.02551 0.01460 -0.0270 0.8487 1.0000
3.500 0.4565 0.02531 0.01457 -0.0264 0.8288 1.0000
3.750 0.4931 0.02491 0.01438 -0.0274 0.8109 1.0000
4.000 0.5203 0.02455 0.01421 -0.0267 0.7888 1.0000
4.250 0.5545 0.02397 0.01395 -0.0268 0.7666 1.0000
4.500 0.5889 0.02342 0.01364 -0.0268 0.7396 1.0000
4.750 0.6264 0.02286 0.01331 -0.0273 0.7054 1.0000
5.000 0.6687 0.02226 0.01289 -0.0283 0.6604 1.0000
5.250 0.7045 0.02203 0.01277 -0.0284 0.6016 1.0000
5.500 0.7313 0.02223 0.01283 -0.0271 0.5361 1.0000
5.750 0.7477 0.02276 0.01317 -0.0244 0.4732 1.0000
6.000 0.7592 0.02348 0.01367 -0.0210 0.4140 1.0000
6.250 0.7680 0.02431 0.01429 -0.0175 0.3584 1.0000
6.500 0.7756 0.02525 0.01501 -0.0140 0.3060 1.0000
6.750 0.7835 0.02626 0.01585 -0.0107 0.2572 1.0000
7.000 0.7913 0.02740 0.01680 -0.0075 0.2127 1.0000
7.250 0.7998 0.02865 0.01787 -0.0046 0.1729 1.0000
7.500 0.8096 0.03001 0.01909 -0.0019 0.1400 1.0000
7.750 0.8207 0.03148 0.02047 0.0005 0.1140 1.0000
8.000 0.8346 0.03307 0.02223 0.0026 0.0952 1.0000
8.250 0.8451 0.03454 0.02369 0.0050 0.0798 1.0000
8.500 0.8647 0.03651 0.02586 0.0064 0.0693 1.0000
8.750 0.8856 0.03875 0.02829 0.0075 0.0614 1.0000
9.000 0.8947 0.04047 0.03003 0.0098 0.0537 1.0000
9.250 0.9134 0.04315 0.03320 0.0113 0.0485 1.0000
9.500 0.9270 0.04601 0.03642 0.0132 0.0452 1.0000
9.750 0.9354 0.04884 0.03949 0.0154 0.0429 1.0000
10.000 0.9371 0.05194 0.04280 0.0182 0.0406 1.0000
10.250 0.9275 0.05463 0.04598 0.0226 0.0387 1.0000
10.500 0.9169 0.05739 0.04908 0.0265 0.0373 1.0000
10.750 0.9037 0.06030 0.05228 0.0300 0.0360 1.0000
11.000 0.8893 0.06354 0.05578 0.0327 0.0354 1.0000
11.250 0.8724 0.06711 0.05957 0.0346 0.0349 1.0000
11.500 0.8528 0.07129 0.06397 0.0356 0.0351 1.0000
11.750 0.8314 0.07606 0.06892 0.0352 0.0354 1.0000
12.000 0.8081 0.08185 0.07486 0.0333 0.0360 1.0000
12.250 0.7846 0.08880 0.08192 0.0297 0.0371 1.0000
12.500 0.7664 0.09598 0.08913 0.0257 0.0386 1.0000
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Polar data table (+)
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