AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 200,000 Max Cl/Cd: 78.94 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k135-il-200000.txt Download as CSV file: xf-ah79k135-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-135/20 B
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2348 0.09211 0.08832 -0.0939 0.8951 0.0521
-10.250 -0.2474 0.08651 0.08277 -0.1010 0.8924 0.0527
-10.000 -0.2582 0.08124 0.07746 -0.1066 0.8895 0.0528
-9.750 -0.2744 0.07742 0.07357 -0.1093 0.8866 0.0529
-9.500 -0.2448 0.07307 0.06936 -0.1062 0.8862 0.0547
-9.250 -0.2425 0.07003 0.06633 -0.1071 0.8845 0.0557
-9.000 -0.2499 0.06637 0.06267 -0.1088 0.8822 0.0563
-8.750 -0.2604 0.06320 0.05948 -0.1091 0.8793 0.0571
-8.500 -0.2742 0.06054 0.05677 -0.1080 0.8764 0.0578
-8.250 -0.2840 0.05795 0.05409 -0.1066 0.8741 0.0590
-8.000 -0.2904 0.05531 0.05133 -0.1054 0.8716 0.0606
-7.750 -0.3117 0.05542 0.05087 -0.1014 0.8684 0.0652
-6.500 -0.2825 0.03299 0.02642 -0.0897 0.8567 0.0317
-6.250 -0.2679 0.02932 0.02252 -0.0884 0.8544 0.0303
-6.000 -0.2497 0.02716 0.02003 -0.0870 0.8520 0.0296
-5.750 -0.2286 0.02542 0.01800 -0.0858 0.8493 0.0293
-5.500 -0.2052 0.02400 0.01634 -0.0849 0.8468 0.0296
-5.250 -0.1806 0.02289 0.01504 -0.0842 0.8446 0.0305
-5.000 -0.1562 0.02216 0.01417 -0.0834 0.8424 0.0319
-4.750 -0.1368 0.02127 0.01334 -0.0824 0.8395 0.0355
-4.500 -0.1167 0.02079 0.01284 -0.0813 0.8361 0.0389
-4.250 -0.0983 0.02001 0.01204 -0.0796 0.8327 0.0439
-4.000 -0.0795 0.01932 0.01139 -0.0780 0.8299 0.0609
-3.750 -0.0595 0.01877 0.01102 -0.0766 0.8275 0.1087
-3.500 -0.0469 0.01839 0.01099 -0.0748 0.8225 0.1681
-3.250 -0.0405 0.01718 0.01090 -0.0719 0.8184 0.4031
-3.000 -0.0342 0.01630 0.01131 -0.0670 0.8153 0.6968
-2.750 -0.0186 0.01685 0.01201 -0.0637 0.8109 0.7798
-2.500 -0.0016 0.01740 0.01251 -0.0609 0.8062 0.8189
-2.250 0.0197 0.01787 0.01285 -0.0587 0.8031 0.8459
-2.000 0.0387 0.01842 0.01333 -0.0562 0.7993 0.8633
-1.750 0.0527 0.01891 0.01376 -0.0532 0.7933 0.8792
-1.500 0.0781 0.01924 0.01398 -0.0516 0.7903 0.8948
-1.250 0.1149 0.01966 0.01429 -0.0516 0.7885 0.9146
-1.000 0.1520 0.02021 0.01479 -0.0532 0.7827 0.9335
-0.750 0.2497 0.02035 0.01475 -0.0662 0.7823 0.9412
-0.500 0.2942 0.02036 0.01467 -0.0696 0.7789 0.9492
-0.250 0.3420 0.02025 0.01445 -0.0735 0.7765 0.9544
0.000 0.3746 0.02028 0.01442 -0.0747 0.7730 0.9612
0.250 0.4140 0.02030 0.01443 -0.0778 0.7668 0.9664
0.500 0.4467 0.02020 0.01428 -0.0789 0.7633 0.9721
0.750 0.4866 0.01999 0.01401 -0.0813 0.7610 0.9753
1.000 0.5183 0.02013 0.01418 -0.0832 0.7538 0.9805
1.250 0.5503 0.01999 0.01402 -0.0843 0.7498 0.9851
1.500 0.5907 0.01966 0.01366 -0.0868 0.7474 0.9879
1.750 0.6226 0.01975 0.01379 -0.0886 0.7405 0.9926
2.000 0.6581 0.01951 0.01357 -0.0904 0.7361 0.9960
2.250 0.6957 0.01910 0.01315 -0.0923 0.7335 0.9989
2.500 0.7151 0.01924 0.01335 -0.0914 0.7260 1.0000
2.750 0.7367 0.01899 0.01312 -0.0903 0.7214 1.0000
3.000 0.7617 0.01857 0.01270 -0.0895 0.7187 1.0000
3.250 0.7747 0.01873 0.01293 -0.0873 0.7101 1.0000
3.500 0.7990 0.01828 0.01251 -0.0864 0.7063 1.0000
3.750 0.8265 0.01766 0.01191 -0.0858 0.7039 1.0000
4.000 0.8397 0.01766 0.01200 -0.0834 0.6942 1.0000
4.250 0.8670 0.01701 0.01137 -0.0829 0.6910 1.0000
4.500 0.8821 0.01695 0.01139 -0.0807 0.6824 1.0000
4.750 0.9081 0.01635 0.01086 -0.0800 0.6781 1.0000
5.000 0.9264 0.01611 0.01069 -0.0782 0.6703 1.0000
5.250 0.9525 0.01543 0.01006 -0.0773 0.6639 1.0000
5.500 0.9708 0.01504 0.00974 -0.0753 0.6533 1.0000
5.750 0.9923 0.01455 0.00932 -0.0738 0.6427 1.0000
6.000 1.0121 0.01401 0.00881 -0.0718 0.6267 1.0000
6.250 1.0317 0.01361 0.00840 -0.0698 0.6084 1.0000
6.500 1.0477 0.01346 0.00822 -0.0673 0.5875 1.0000
6.750 1.0609 0.01344 0.00813 -0.0643 0.5627 1.0000
7.000 1.0677 0.01361 0.00821 -0.0603 0.5346 1.0000
7.250 1.0686 0.01391 0.00836 -0.0553 0.5005 1.0000
7.500 1.0667 0.01435 0.00862 -0.0500 0.4635 1.0000
7.750 1.0666 0.01495 0.00903 -0.0453 0.4244 1.0000
8.000 1.0659 0.01566 0.00957 -0.0407 0.3877 1.0000
8.250 1.0602 0.01660 0.01030 -0.0357 0.3457 1.0000
8.500 1.0528 0.01792 0.01138 -0.0312 0.2989 1.0000
8.750 1.0421 0.01981 0.01291 -0.0272 0.2402 1.0000
9.000 1.0295 0.02208 0.01471 -0.0234 0.1697 1.0000
9.250 1.0123 0.02484 0.01682 -0.0193 0.0827 1.0000
9.500 1.0009 0.02746 0.01906 -0.0158 0.0437 1.0000
9.750 1.0047 0.02911 0.02075 -0.0138 0.0356 1.0000
10.000 1.0077 0.03085 0.02257 -0.0118 0.0325 1.0000
10.250 1.0141 0.03236 0.02419 -0.0103 0.0304 1.0000
10.500 1.0204 0.03392 0.02582 -0.0088 0.0286 1.0000
10.750 1.0239 0.03571 0.02766 -0.0074 0.0269 1.0000
11.000 1.0224 0.03799 0.02997 -0.0055 0.0255 1.0000
11.250 1.0289 0.03969 0.03177 -0.0043 0.0251 1.0000
11.500 1.0368 0.04135 0.03351 -0.0030 0.0245 1.0000
11.750 1.0463 0.04297 0.03521 -0.0018 0.0239 1.0000
12.000 1.0592 0.04446 0.03677 -0.0007 0.0234 1.0000
12.250 1.0761 0.04582 0.03819 0.0003 0.0231 1.0000
12.500 1.0976 0.04717 0.03965 0.0012 0.0229 1.0000
12.750 1.1212 0.04872 0.04133 0.0020 0.0226 1.0000
13.000 1.1455 0.05072 0.04357 0.0027 0.0228 1.0000
13.250 1.1630 0.05324 0.04634 0.0034 0.0229 1.0000
13.500 1.1731 0.05617 0.04955 0.0044 0.0231 1.0000
13.750 1.1760 0.05940 0.05306 0.0054 0.0232 1.0000
14.000 1.1732 0.06243 0.05632 0.0063 0.0227 1.0000
14.250 1.1676 0.06604 0.06019 0.0071 0.0228 1.0000
14.500 1.1581 0.07030 0.06473 0.0078 0.0231 1.0000
14.750 1.1467 0.07486 0.06955 0.0081 0.0237 1.0000
15.000 1.1320 0.07971 0.07463 0.0079 0.0240 1.0000
15.250 1.1161 0.08494 0.08008 0.0073 0.0244 1.0000
15.500 1.0984 0.09053 0.08587 0.0062 0.0247 1.0000
15.750 1.1062 0.09510 0.09052 0.0060 0.0261 1.0000
16.000 1.0811 0.10048 0.09618 0.0037 0.0266 1.0000
16.250 1.0338 0.11058 0.10666 -0.0018 0.0274 1.0000
16.500 1.0002 0.12047 0.11678 -0.0077 0.0277 1.0000
16.750 0.9581 0.13378 0.13032 -0.0164 0.0284 1.0000
17.000 0.9033 0.15408 0.15074 -0.0290 0.0310 1.0000
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