AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 200,000 Max Cl/Cd: 76.22 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k143-il-200000.txt Download as CSV file: xf-ah79k143-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-143/18
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2785 0.12619 0.12220 -0.0763 0.9062 0.0472
-12.750 -0.2815 0.12169 0.11772 -0.0827 0.9053 0.0483
-12.500 -0.2851 0.11652 0.11258 -0.0890 0.9042 0.0487
-12.250 -0.2726 0.11147 0.10752 -0.0888 0.9033 0.0495
-12.000 -0.2568 0.10844 0.10446 -0.0892 0.9019 0.0504
-11.750 -0.2429 0.10554 0.10154 -0.0904 0.9005 0.0521
-11.500 -0.2345 0.10188 0.09787 -0.0932 0.8994 0.0528
-11.250 -0.1623 0.07857 0.07486 -0.1072 0.8934 0.0604
-11.000 -0.1357 0.07681 0.07307 -0.1040 0.8924 0.0623
-10.750 -0.1231 0.07483 0.07108 -0.1037 0.8913 0.0659
-10.500 -0.1282 0.07055 0.06682 -0.1058 0.8901 0.0692
-10.250 -0.2596 0.07239 0.06846 -0.1217 0.8927 0.0613
-10.000 -0.2270 0.07395 0.07005 -0.1159 0.8919 0.0640
-9.750 -0.2346 0.06852 0.06463 -0.1209 0.8903 0.0651
-9.500 -0.2562 0.06303 0.05908 -0.1245 0.8882 0.0642
-9.250 -0.2666 0.06001 0.05602 -0.1242 0.8858 0.0657
-9.000 -0.2834 0.05729 0.05322 -0.1222 0.8833 0.0669
-8.750 -0.3003 0.05496 0.05078 -0.1190 0.8813 0.0680
-8.500 -0.3725 0.04227 0.03705 -0.1087 0.8785 0.0375
-8.250 -0.3767 0.03913 0.03367 -0.1050 0.8761 0.0359
-8.000 -0.3765 0.03690 0.03111 -0.1014 0.8738 0.0369
-7.750 -0.3731 0.03414 0.02800 -0.0981 0.8717 0.0359
-7.500 -0.3640 0.03213 0.02564 -0.0954 0.8693 0.0363
-7.250 -0.3513 0.02977 0.02285 -0.0930 0.8669 0.0362
-7.000 -0.3346 0.02807 0.02077 -0.0911 0.8650 0.0370
-6.750 -0.3173 0.02671 0.01914 -0.0893 0.8628 0.0378
-6.500 -0.2993 0.02590 0.01805 -0.0876 0.8598 0.0390
-6.250 -0.2769 0.02422 0.01639 -0.0871 0.8572 0.0424
-6.000 -0.2562 0.02396 0.01602 -0.0860 0.8543 0.0471
-5.750 -0.2313 0.02295 0.01494 -0.0855 0.8520 0.0511
-5.500 -0.2099 0.02271 0.01468 -0.0846 0.8496 0.0563
-5.250 -0.1942 0.02247 0.01437 -0.0826 0.8458 0.0600
-5.000 -0.1775 0.02181 0.01381 -0.0809 0.8425 0.0667
-4.750 -0.1588 0.02140 0.01338 -0.0793 0.8396 0.0752
-4.500 -0.1394 0.02113 0.01314 -0.0778 0.8371 0.0899
-4.250 -0.1340 0.02101 0.01314 -0.0743 0.8315 0.1070
-4.000 -0.1185 0.02075 0.01301 -0.0723 0.8280 0.1367
-3.750 -0.0998 0.02041 0.01292 -0.0709 0.8254 0.1881
-3.500 -0.1002 0.02028 0.01314 -0.0665 0.8186 0.2544
-3.250 -0.0966 0.01938 0.01310 -0.0626 0.8148 0.4424
-3.000 -0.1039 0.01898 0.01395 -0.0554 0.8089 0.7008
-2.750 -0.0805 0.02021 0.01538 -0.0521 0.8048 0.8078
-2.500 -0.0568 0.02110 0.01614 -0.0497 0.8020 0.8408
-2.250 -0.0535 0.02192 0.01692 -0.0447 0.7947 0.8593
-2.000 -0.0276 0.02261 0.01749 -0.0432 0.7910 0.8768
-1.750 0.0202 0.02317 0.01791 -0.0456 0.7892 0.8900
-1.500 0.0822 0.02362 0.01819 -0.0510 0.7882 0.9008
-1.250 0.1465 0.02393 0.01836 -0.0574 0.7873 0.9114
-1.000 0.2641 0.02410 0.01837 -0.0739 0.7878 0.9275
-0.750 0.3174 0.02421 0.01843 -0.0792 0.7837 0.9414
-0.500 0.3381 0.02433 0.01852 -0.0783 0.7782 0.9505
-0.250 0.3822 0.02405 0.01817 -0.0818 0.7757 0.9537
0.000 0.4193 0.02389 0.01795 -0.0838 0.7736 0.9582
0.250 0.4398 0.02404 0.01812 -0.0835 0.7663 0.9649
0.500 0.4732 0.02386 0.01791 -0.0850 0.7625 0.9690
0.750 0.5022 0.02369 0.01771 -0.0854 0.7599 0.9734
1.000 0.5401 0.02344 0.01745 -0.0877 0.7573 0.9764
1.250 0.5591 0.02364 0.01769 -0.0872 0.7492 0.9820
1.500 0.5974 0.02332 0.01737 -0.0895 0.7465 0.9849
1.750 0.6337 0.02295 0.01700 -0.0912 0.7444 0.9882
2.000 0.6611 0.02306 0.01717 -0.0923 0.7368 0.9924
2.250 0.6955 0.02274 0.01687 -0.0939 0.7330 0.9954
2.500 0.7328 0.02226 0.01642 -0.0958 0.7308 0.9979
2.750 0.7683 0.02179 0.01596 -0.0973 0.7289 1.0000
3.000 0.7771 0.02209 0.01634 -0.0946 0.7192 1.0000
3.250 0.8026 0.02167 0.01596 -0.0939 0.7168 1.0000
3.500 0.8144 0.02187 0.01623 -0.0915 0.7089 1.0000
3.750 0.8383 0.02143 0.01583 -0.0906 0.7049 1.0000
4.000 0.8667 0.02071 0.01516 -0.0902 0.7025 1.0000
4.250 0.8945 0.02006 0.01457 -0.0899 0.7004 1.0000
4.500 0.9038 0.02033 0.01493 -0.0870 0.6906 1.0000
4.750 0.9334 0.01952 0.01419 -0.0867 0.6883 1.0000
5.000 0.9505 0.01929 0.01405 -0.0847 0.6807 1.0000
5.250 0.9797 0.01833 0.01316 -0.0843 0.6755 1.0000
5.500 1.0080 0.01720 0.01209 -0.0835 0.6668 1.0000
5.750 1.0432 0.01579 0.01068 -0.0838 0.6572 1.0000
6.000 1.0621 0.01525 0.01020 -0.0816 0.6403 1.0000
6.250 1.0810 0.01471 0.00965 -0.0793 0.6157 1.0000
6.500 1.0966 0.01448 0.00933 -0.0765 0.5858 1.0000
6.750 1.1083 0.01454 0.00928 -0.0733 0.5549 1.0000
7.000 1.1138 0.01483 0.00944 -0.0690 0.5191 1.0000
7.250 1.1132 0.01529 0.00976 -0.0638 0.4818 1.0000
7.500 1.1021 0.01593 0.01019 -0.0567 0.4417 1.0000
7.750 1.0859 0.01654 0.01067 -0.0489 0.4095 1.0000
8.000 1.0612 0.01704 0.01107 -0.0396 0.3855 1.0000
8.250 1.0354 0.01772 0.01164 -0.0308 0.3587 1.0000
8.500 1.0103 0.01870 0.01246 -0.0230 0.3286 1.0000
8.750 0.9873 0.01987 0.01341 -0.0159 0.2899 1.0000
9.000 0.9647 0.02156 0.01474 -0.0096 0.2321 1.0000
9.250 0.9409 0.02397 0.01658 -0.0042 0.1520 1.0000
9.500 0.9256 0.02637 0.01848 -0.0003 0.0876 1.0000
9.750 0.9178 0.02857 0.02045 0.0029 0.0621 1.0000
10.000 0.9199 0.03023 0.02214 0.0049 0.0532 1.0000
10.250 0.9184 0.03222 0.02413 0.0071 0.0475 1.0000
10.500 0.9242 0.03376 0.02574 0.0086 0.0427 1.0000
10.750 0.9220 0.03594 0.02789 0.0106 0.0393 1.0000
11.000 0.9321 0.03730 0.02932 0.0118 0.0377 1.0000
11.250 0.9432 0.03862 0.03071 0.0128 0.0366 1.0000
11.500 0.9552 0.03997 0.03209 0.0140 0.0344 1.0000
11.750 0.9697 0.04117 0.03329 0.0149 0.0330 1.0000
12.000 1.0033 0.04215 0.03415 0.0157 0.0310 1.0000
12.250 1.0186 0.04335 0.03551 0.0163 0.0302 1.0000
12.500 1.0393 0.04464 0.03697 0.0170 0.0291 1.0000
12.750 1.0657 0.04614 0.03864 0.0173 0.0288 1.0000
13.000 1.0873 0.04799 0.04069 0.0178 0.0283 1.0000
13.250 1.1055 0.05027 0.04323 0.0185 0.0281 1.0000
13.500 1.1178 0.05308 0.04632 0.0194 0.0281 1.0000
13.750 1.1243 0.05621 0.04974 0.0205 0.0286 1.0000
14.000 1.1255 0.05963 0.05343 0.0216 0.0289 1.0000
14.250 1.1219 0.06336 0.05743 0.0227 0.0293 1.0000
14.500 1.1156 0.06770 0.06201 0.0237 0.0300 1.0000
14.750 1.1006 0.07120 0.06576 0.0246 0.0297 1.0000
15.000 1.0842 0.07498 0.06977 0.0251 0.0294 1.0000
15.250 1.0695 0.07974 0.07473 0.0251 0.0299 1.0000
15.500 1.0528 0.08488 0.08006 0.0247 0.0302 1.0000
15.750 1.0630 0.08910 0.08436 0.0247 0.0314 1.0000
16.000 0.9664 0.10315 0.09916 0.0198 0.0374 1.0000
16.250 0.9419 0.10956 0.10575 0.0156 0.0353 1.0000
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