MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 50,000 Max Cl/Cd: 21.25 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh104-il-50000-n5.txt Download as CSV file: xf-mh104-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5731 0.10065 0.09391 -0.0176 1.0000 0.0412
-12.000 -0.5964 0.09110 0.08431 -0.0237 1.0000 0.0405
-11.750 -0.6208 0.08233 0.07542 -0.0297 1.0000 0.0397
-11.500 -0.6472 0.07433 0.06724 -0.0353 1.0000 0.0389
-11.250 -0.6691 0.06813 0.06088 -0.0392 1.0000 0.0386
-11.000 -0.6862 0.06328 0.05583 -0.0414 1.0000 0.0387
-10.750 -0.6995 0.05922 0.05155 -0.0421 1.0000 0.0389
-10.500 -0.7079 0.05588 0.04798 -0.0419 1.0000 0.0392
-10.250 -0.7136 0.05277 0.04463 -0.0408 1.0000 0.0398
-10.000 -0.7146 0.05001 0.04164 -0.0393 1.0000 0.0404
-9.750 -0.7117 0.04737 0.03873 -0.0376 1.0000 0.0415
-9.500 -0.7046 0.04498 0.03599 -0.0361 1.0000 0.0430
-9.250 -0.6938 0.04292 0.03398 -0.0350 1.0000 0.0453
-9.000 -0.6824 0.04108 0.03205 -0.0338 1.0000 0.0480
-8.750 -0.6685 0.03915 0.02991 -0.0324 1.0000 0.0514
-8.500 -0.6559 0.03732 0.02807 -0.0309 1.0000 0.0547
-8.250 -0.6450 0.03573 0.02644 -0.0293 1.0000 0.0597
-8.000 -0.6341 0.03412 0.02478 -0.0275 1.0000 0.0654
-7.750 -0.6250 0.03265 0.02333 -0.0255 1.0000 0.0727
-7.500 -0.6189 0.03120 0.02199 -0.0232 1.0000 0.0819
-7.250 -0.6171 0.02994 0.02086 -0.0201 1.0000 0.0938
-7.000 -0.5995 0.02811 0.01931 -0.0204 0.9765 0.1232
-6.750 -0.5703 0.02637 0.01804 -0.0226 0.9462 0.1948
-6.500 -0.5392 0.02570 0.01740 -0.0242 0.9205 0.2623
-6.250 -0.5117 0.02545 0.01710 -0.0245 0.8968 0.3092
-6.000 -0.4870 0.02534 0.01691 -0.0239 0.8749 0.3448
-5.750 -0.4636 0.02516 0.01657 -0.0229 0.8542 0.3727
-5.500 -0.4395 0.02493 0.01617 -0.0218 0.8355 0.3948
-5.250 -0.4160 0.02465 0.01567 -0.0206 0.8181 0.4152
-5.000 -0.3924 0.02437 0.01522 -0.0194 0.8018 0.4340
-4.750 -0.3683 0.02410 0.01480 -0.0183 0.7863 0.4521
-4.500 -0.3441 0.02385 0.01441 -0.0173 0.7715 0.4704
-4.250 -0.3197 0.02360 0.01404 -0.0163 0.7573 0.4895
-4.000 -0.2954 0.02338 0.01368 -0.0154 0.7438 0.5095
-3.750 -0.2706 0.02317 0.01336 -0.0145 0.7312 0.5300
-3.500 -0.2453 0.02298 0.01309 -0.0136 0.7199 0.5511
-3.250 -0.2206 0.02281 0.01283 -0.0127 0.7082 0.5744
-3.000 -0.1952 0.02269 0.01269 -0.0119 0.6966 0.5977
-2.750 -0.1705 0.02259 0.01252 -0.0109 0.6865 0.6238
-2.500 -0.1444 0.02252 0.01243 -0.0100 0.6767 0.6500
-2.250 -0.1179 0.02251 0.01242 -0.0093 0.6663 0.6780
-2.000 -0.0900 0.02251 0.01236 -0.0086 0.6579 0.7076
-1.750 -0.0607 0.02261 0.01245 -0.0083 0.6480 0.7378
-1.500 -0.0292 0.02273 0.01252 -0.0084 0.6395 0.7682
-1.250 0.0046 0.02291 0.01263 -0.0088 0.6308 0.7981
-1.000 0.0429 0.02317 0.01280 -0.0102 0.6223 0.8249
-0.750 0.0819 0.02341 0.01292 -0.0117 0.6144 0.8504
-0.500 0.1209 0.02371 0.01311 -0.0136 0.6062 0.8749
-0.250 0.1641 0.02396 0.01321 -0.0162 0.5987 0.8958
0.000 0.2089 0.02425 0.01339 -0.0194 0.5907 0.9153
0.250 0.2521 0.02446 0.01348 -0.0224 0.5836 0.9349
0.500 0.2940 0.02468 0.01361 -0.0254 0.5765 0.9544
0.750 0.3401 0.02484 0.01369 -0.0295 0.5691 0.9714
1.000 0.3866 0.02490 0.01364 -0.0336 0.5630 0.9877
1.250 0.4273 0.02511 0.01385 -0.0372 0.5555 1.0000
1.500 0.4452 0.02527 0.01391 -0.0360 0.5507 1.0000
1.750 0.4624 0.02569 0.01434 -0.0351 0.5445 1.0000
2.000 0.4801 0.02607 0.01469 -0.0340 0.5387 1.0000
2.250 0.4993 0.02630 0.01485 -0.0328 0.5344 1.0000
2.500 0.5159 0.02695 0.01554 -0.0319 0.5279 1.0000
2.750 0.5340 0.02739 0.01597 -0.0307 0.5224 1.0000
3.000 0.5544 0.02764 0.01614 -0.0295 0.5184 1.0000
3.250 0.5692 0.02853 0.01714 -0.0285 0.5115 1.0000
3.500 0.5878 0.02901 0.01761 -0.0273 0.5063 1.0000
3.750 0.6094 0.02924 0.01777 -0.0261 0.5024 1.0000
4.000 0.6212 0.03041 0.01908 -0.0249 0.4949 1.0000
4.250 0.6407 0.03086 0.01953 -0.0236 0.4899 1.0000
4.500 0.6592 0.03144 0.02013 -0.0224 0.4850 1.0000
4.750 0.6711 0.03257 0.02136 -0.0210 0.4779 1.0000
5.000 0.6925 0.03290 0.02169 -0.0199 0.4734 1.0000
5.250 0.7037 0.03409 0.02298 -0.0184 0.4667 1.0000
5.500 0.7188 0.03493 0.02388 -0.0170 0.4606 1.0000
5.750 0.7439 0.03500 0.02394 -0.0160 0.4566 1.0000
6.000 0.7439 0.03699 0.02611 -0.0139 0.4479 1.0000
6.250 0.7657 0.03730 0.02644 -0.0128 0.4430 1.0000
6.500 0.7697 0.03895 0.02820 -0.0109 0.4354 1.0000
6.750 0.7839 0.03981 0.02913 -0.0094 0.4291 1.0000
7.000 0.8154 0.03944 0.02878 -0.0087 0.4254 1.0000
7.250 0.7981 0.04255 0.03204 -0.0059 0.4148 1.0000
7.500 0.8304 0.04208 0.03162 -0.0052 0.4108 1.0000
7.750 0.8061 0.04568 0.03532 -0.0023 0.3998 1.0000
8.000 0.8405 0.04500 0.03472 -0.0016 0.3958 1.0000
8.250 0.8029 0.04955 0.03929 0.0015 0.3840 1.0000
8.500 0.7953 0.05203 0.04181 0.0031 0.3756 1.0000
8.750 0.7960 0.05408 0.04393 0.0042 0.3673 1.0000
9.000 0.8330 0.05276 0.04271 0.0056 0.3639 1.0000
9.250 0.8011 0.05821 0.04817 0.0058 0.3509 1.0000
9.750 0.7673 0.06732 0.05733 0.0050 0.3276 1.0000
10.250 0.7723 0.07217 0.06230 0.0054 0.3106 1.0000
10.500 0.8008 0.07128 0.06155 0.0070 0.3062 1.0000
10.750 0.7824 0.07650 0.06678 0.0059 0.2945 1.0000
11.000 0.7996 0.07709 0.06749 0.0067 0.2888 1.0000
11.250 0.7944 0.08067 0.07112 0.0062 0.2788 1.0000
11.750 0.8052 0.08514 0.07575 0.0063 0.2636 1.0000
12.250 0.8166 0.08955 0.08034 0.0062 0.2485 1.0000
12.750 0.8265 0.09428 0.08525 0.0060 0.2337 1.0000
13.000 0.8027 0.10152 0.09250 0.0033 0.2228 1.0000
13.250 0.8332 0.09963 0.09077 0.0052 0.2191 1.0000
13.500 0.8061 0.10779 0.09892 0.0020 0.2081 1.0000
13.750 0.8347 0.10607 0.09735 0.0038 0.2042 1.0000
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Polar data table (+)
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