AH 81-131 (ah81131-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 50,000 Max Cl/Cd: 21.53 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81131-il-50000-n5.txt Download as CSV file: xf-ah81131-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-131
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2091 0.10992 0.10397 -0.0605 0.9051 0.1306
-10.750 -0.2287 0.10778 0.10189 -0.0640 0.9038 0.1373
-10.500 -0.2178 0.10341 0.09753 -0.0647 0.9020 0.1389
-10.250 -0.2152 0.09449 0.08847 -0.0702 0.9005 0.0660
-9.750 -0.3107 0.09229 0.08600 -0.0771 0.9046 0.0542
-9.500 -0.3017 0.08881 0.08252 -0.0773 0.9025 0.0529
-9.250 -0.2999 0.08477 0.07849 -0.0801 0.8996 0.0516
-9.000 -0.3033 0.08062 0.07434 -0.0829 0.8965 0.0503
-8.750 -0.3097 0.07697 0.07064 -0.0848 0.8932 0.0486
-8.500 -0.3210 0.07368 0.06728 -0.0852 0.8899 0.0472
-8.250 -0.3343 0.07089 0.06440 -0.0846 0.8862 0.0459
-8.000 -0.3471 0.06800 0.06133 -0.0833 0.8824 0.0446
-7.750 -0.3659 0.06663 0.05933 -0.0799 0.8782 0.0417
-7.500 -0.3652 0.06378 0.05633 -0.0782 0.8753 0.0414
-7.250 -0.3652 0.06123 0.05366 -0.0761 0.8719 0.0409
-7.000 -0.3643 0.05881 0.05106 -0.0737 0.8685 0.0404
-6.750 -0.3617 0.05645 0.04846 -0.0713 0.8654 0.0399
-6.500 -0.3576 0.05422 0.04593 -0.0687 0.8626 0.0395
-6.250 -0.3568 0.05239 0.04384 -0.0654 0.8590 0.0391
-6.000 -0.3520 0.05046 0.04160 -0.0624 0.8555 0.0389
-5.750 -0.3426 0.04850 0.03928 -0.0598 0.8526 0.0386
-5.500 -0.3287 0.04651 0.03688 -0.0577 0.8501 0.0385
-5.250 -0.3218 0.04504 0.03508 -0.0545 0.8467 0.0386
-5.000 -0.3096 0.04353 0.03323 -0.0520 0.8435 0.0387
-4.750 -0.2906 0.04193 0.03124 -0.0503 0.8406 0.0391
-4.500 -0.2654 0.04038 0.02927 -0.0496 0.8383 0.0397
-4.250 -0.2357 0.03913 0.02762 -0.0495 0.8365 0.0414
-4.000 -0.2196 0.03796 0.02644 -0.0481 0.8333 0.0443
-3.750 -0.1982 0.03716 0.02553 -0.0471 0.8302 0.0485
-3.500 -0.1713 0.03635 0.02447 -0.0468 0.8276 0.0525
-3.250 -0.1458 0.03553 0.02346 -0.0464 0.8253 0.0568
-3.000 0.0637 0.03213 0.02330 -0.0716 0.8325 0.9470
-2.750 0.1104 0.03221 0.02288 -0.0762 0.8302 0.9650
-2.500 0.1579 0.03220 0.02244 -0.0812 0.8282 0.9811
-2.250 0.2061 0.03211 0.02199 -0.0864 0.8262 0.9947
-2.000 0.2364 0.03216 0.02178 -0.0881 0.8238 1.0000
-1.750 0.2382 0.03260 0.02210 -0.0852 0.8191 1.0000
-1.500 0.2445 0.03300 0.02233 -0.0827 0.8148 1.0000
-1.250 0.2583 0.03334 0.02251 -0.0811 0.8114 1.0000
-1.000 0.2637 0.03382 0.02286 -0.0783 0.8070 1.0000
-0.750 0.2667 0.03431 0.02325 -0.0751 0.8021 1.0000
-0.500 0.2815 0.03472 0.02352 -0.0736 0.7983 1.0000
-0.250 0.2884 0.03523 0.02393 -0.0708 0.7937 1.0000
0.000 0.2927 0.03574 0.02433 -0.0676 0.7881 1.0000
0.250 0.3129 0.03614 0.02461 -0.0668 0.7841 1.0000
0.500 0.3133 0.03669 0.02508 -0.0629 0.7772 1.0000
0.750 0.3303 0.03711 0.02541 -0.0615 0.7721 1.0000
1.000 0.3407 0.03760 0.02583 -0.0591 0.7662 1.0000
1.250 0.3510 0.03808 0.02625 -0.0566 0.7598 1.0000
1.500 0.3787 0.03847 0.02657 -0.0568 0.7560 1.0000
2.000 0.4008 0.03946 0.02748 -0.0521 0.7431 1.0000
2.250 0.3975 0.04002 0.02801 -0.0476 0.7345 1.0000
2.500 0.4237 0.04044 0.02844 -0.0476 0.7299 1.0000
3.000 0.4491 0.04142 0.02940 -0.0434 0.7166 1.0000
3.250 0.4514 0.04199 0.02995 -0.0399 0.7078 1.0000
3.500 0.4779 0.04240 0.03040 -0.0398 0.7029 1.0000
3.750 0.4809 0.04299 0.03099 -0.0365 0.6937 1.0000
4.000 0.5099 0.04334 0.03144 -0.0368 0.6890 1.0000
4.250 0.5129 0.04396 0.03208 -0.0336 0.6791 1.0000
4.500 0.5301 0.04443 0.03261 -0.0322 0.6719 1.0000
4.750 0.5482 0.04485 0.03310 -0.0310 0.6642 1.0000
5.000 0.5587 0.04538 0.03370 -0.0289 0.6545 1.0000
5.250 0.5897 0.04545 0.03395 -0.0290 0.6488 1.0000
5.500 0.5983 0.04597 0.03453 -0.0266 0.6376 1.0000
5.750 0.6106 0.04643 0.03508 -0.0247 0.6271 1.0000
6.000 0.6320 0.04660 0.03539 -0.0237 0.6185 1.0000
6.250 0.6533 0.04675 0.03569 -0.0226 0.6096 1.0000
6.500 0.6650 0.04725 0.03630 -0.0207 0.5981 1.0000
6.750 0.6796 0.04765 0.03692 -0.0191 0.5872 1.0000
7.000 0.7090 0.04737 0.03685 -0.0186 0.5801 1.0000
7.250 0.7234 0.04773 0.03739 -0.0169 0.5684 1.0000
7.500 0.7365 0.04819 0.03803 -0.0151 0.5560 1.0000
7.750 0.7512 0.04856 0.03859 -0.0135 0.5437 1.0000
8.000 0.7680 0.04875 0.03907 -0.0119 0.5314 1.0000
8.250 0.7882 0.04843 0.03899 -0.0102 0.5177 1.0000
8.500 0.8172 0.04577 0.03659 -0.0073 0.4949 1.0000
8.750 0.8398 0.04317 0.03415 -0.0035 0.4587 1.0000
9.000 0.8609 0.04201 0.03311 -0.0009 0.4239 1.0000
9.250 0.8826 0.04121 0.03244 0.0014 0.3853 1.0000
9.500 0.8938 0.04152 0.03270 0.0040 0.3353 1.0000
9.750 0.8976 0.04244 0.03317 0.0070 0.2660 1.0000
10.000 0.8926 0.04455 0.03480 0.0096 0.2096 1.0000
10.250 0.8873 0.04700 0.03688 0.0117 0.1690 1.0000
10.500 0.8860 0.04933 0.03900 0.0134 0.1451 1.0000
10.750 0.8882 0.05147 0.04103 0.0150 0.1300 1.0000
11.000 0.8937 0.05340 0.04292 0.0165 0.1184 1.0000
11.250 0.9003 0.05529 0.04481 0.0178 0.1072 1.0000
11.500 0.9085 0.05709 0.04662 0.0191 0.0973 1.0000
11.750 0.9242 0.05845 0.04805 0.0206 0.0886 1.0000
12.000 0.9354 0.06028 0.05005 0.0218 0.0778 1.0000
12.250 0.9488 0.06222 0.05223 0.0230 0.0671 1.0000
12.500 0.9555 0.06463 0.05474 0.0239 0.0577 1.0000
12.750 0.9632 0.06699 0.05708 0.0248 0.0501 1.0000
13.000 0.9660 0.07024 0.06077 0.0257 0.0437 1.0000
13.250 0.9683 0.07311 0.06377 0.0262 0.0399 1.0000
13.500 0.9700 0.07645 0.06725 0.0267 0.0368 1.0000
13.750 0.9632 0.08077 0.07199 0.0268 0.0347 1.0000
14.000 0.9556 0.08533 0.07687 0.0266 0.0334 1.0000
14.250 0.9454 0.09029 0.08210 0.0259 0.0328 1.0000
14.500 0.9313 0.09589 0.08796 0.0246 0.0324 1.0000
14.750 0.9147 0.10216 0.09446 0.0224 0.0322 1.0000
15.000 0.8965 0.10907 0.10158 0.0195 0.0325 1.0000
15.250 0.8763 0.11699 0.10967 0.0156 0.0328 1.0000
15.500 0.8553 0.12590 0.11871 0.0109 0.0335 1.0000
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Polar data table (+)
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