AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.68 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k135-il-1000000-n5.txt Download as CSV file: xf-ah79k135-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3364 0.09288 0.09007 -0.0750 0.7551 0.0051
-11.500 -0.5361 0.04238 0.03934 -0.1032 0.7532 0.0046
-11.250 -0.5696 0.03735 0.03408 -0.1020 0.7520 0.0046
-11.000 -0.5857 0.03440 0.03094 -0.0993 0.7509 0.0046
-10.750 -0.6052 0.03156 0.02788 -0.0949 0.7498 0.0046
-10.500 -0.6120 0.02986 0.02600 -0.0909 0.7488 0.0047
-10.250 -0.6148 0.02765 0.02351 -0.0875 0.7477 0.0047
-10.000 -0.6050 0.02640 0.02211 -0.0856 0.7466 0.0047
-9.750 -0.5999 0.02438 0.01983 -0.0830 0.7457 0.0047
-9.500 -0.5871 0.02302 0.01828 -0.0813 0.7449 0.0048
-9.250 -0.5733 0.02161 0.01668 -0.0796 0.7441 0.0048
-9.000 -0.5555 0.02064 0.01557 -0.0785 0.7432 0.0048
-8.750 -0.5385 0.01940 0.01415 -0.0771 0.7422 0.0048
-8.500 -0.5186 0.01851 0.01313 -0.0762 0.7412 0.0049
-8.250 -0.4968 0.01785 0.01234 -0.0754 0.7401 0.0049
-8.000 -0.4745 0.01721 0.01160 -0.0748 0.7392 0.0049
-7.750 -0.4536 0.01625 0.01051 -0.0739 0.7383 0.0050
-7.500 -0.4338 0.01512 0.00922 -0.0728 0.7372 0.0051
-7.250 -0.4115 0.01438 0.00839 -0.0721 0.7362 0.0052
-7.000 -0.3889 0.01369 0.00761 -0.0714 0.7352 0.0052
-6.750 -0.3655 0.01312 0.00696 -0.0708 0.7342 0.0053
-6.500 -0.3413 0.01267 0.00644 -0.0703 0.7332 0.0053
-6.250 -0.3174 0.01218 0.00588 -0.0697 0.7320 0.0054
-6.000 -0.2929 0.01174 0.00541 -0.0693 0.7310 0.0056
-5.750 -0.2678 0.01137 0.00501 -0.0690 0.7298 0.0057
-5.500 -0.2424 0.01103 0.00463 -0.0687 0.7285 0.0059
-5.250 -0.2167 0.01072 0.00430 -0.0684 0.7271 0.0062
-5.000 -0.1908 0.01045 0.00399 -0.0682 0.7257 0.0064
-4.750 -0.1646 0.01019 0.00371 -0.0680 0.7243 0.0068
-4.500 -0.1382 0.00996 0.00344 -0.0678 0.7229 0.0071
-4.250 -0.1118 0.00972 0.00318 -0.0677 0.7215 0.0077
-4.000 -0.0853 0.00951 0.00294 -0.0676 0.7201 0.0085
-3.500 -0.0316 0.00916 0.00255 -0.0674 0.7172 0.0120
-3.250 -0.0057 0.00886 0.00237 -0.0672 0.7156 0.0299
-3.000 0.0213 0.00870 0.00224 -0.0672 0.7137 0.0412
-2.750 0.0484 0.00853 0.00212 -0.0672 0.7117 0.0515
-2.500 0.0750 0.00832 0.00200 -0.0672 0.7097 0.0734
-2.250 0.1012 0.00806 0.00187 -0.0671 0.7077 0.1133
-2.000 0.1268 0.00774 0.00174 -0.0669 0.7058 0.1720
-1.750 0.1529 0.00750 0.00163 -0.0668 0.7038 0.2243
-1.500 0.1788 0.00722 0.00155 -0.0667 0.7015 0.2851
-1.250 0.2048 0.00695 0.00148 -0.0666 0.6987 0.3472
-1.000 0.2303 0.00663 0.00140 -0.0664 0.6956 0.4235
-0.750 0.2537 0.00616 0.00129 -0.0658 0.6926 0.5427
-0.500 0.2767 0.00573 0.00122 -0.0651 0.6900 0.6577
-0.250 0.3016 0.00551 0.00124 -0.0646 0.6869 0.7293
0.000 0.3280 0.00542 0.00128 -0.0643 0.6832 0.7733
0.250 0.3551 0.00539 0.00131 -0.0641 0.6793 0.7985
0.500 0.3821 0.00540 0.00135 -0.0639 0.6754 0.8197
0.750 0.4101 0.00543 0.00139 -0.0640 0.6707 0.8318
1.000 0.4378 0.00545 0.00142 -0.0640 0.6652 0.8393
1.250 0.4658 0.00549 0.00143 -0.0642 0.6597 0.8457
1.500 0.4935 0.00552 0.00147 -0.0642 0.6525 0.8497
1.750 0.5211 0.00556 0.00149 -0.0642 0.6450 0.8537
2.000 0.5486 0.00562 0.00152 -0.0643 0.6356 0.8579
2.250 0.5759 0.00569 0.00155 -0.0643 0.6246 0.8611
2.500 0.6021 0.00578 0.00160 -0.0641 0.6098 0.8634
2.750 0.6280 0.00591 0.00167 -0.0638 0.5936 0.8657
3.000 0.6539 0.00604 0.00176 -0.0636 0.5789 0.8681
3.250 0.6799 0.00617 0.00186 -0.0634 0.5653 0.8707
3.500 0.7058 0.00632 0.00196 -0.0632 0.5514 0.8731
3.750 0.7295 0.00657 0.00210 -0.0626 0.5257 0.8755
4.000 0.7519 0.00685 0.00228 -0.0617 0.4963 0.8776
4.250 0.7722 0.00723 0.00252 -0.0605 0.4590 0.8799
4.500 0.7887 0.00780 0.00283 -0.0586 0.4035 0.8826
4.750 0.8050 0.00837 0.00316 -0.0568 0.3520 0.8855
5.000 0.8225 0.00887 0.00346 -0.0551 0.3102 0.8883
5.250 0.8393 0.00938 0.00379 -0.0534 0.2704 0.8908
5.500 0.8545 0.00990 0.00414 -0.0514 0.2307 0.8935
5.750 0.8707 0.01037 0.00448 -0.0495 0.2006 0.8964
6.000 0.8809 0.01104 0.00493 -0.0467 0.1557 0.8999
6.250 0.8923 0.01162 0.00536 -0.0440 0.1214 0.9031
6.500 0.8965 0.01223 0.00581 -0.0400 0.0874 0.9067
6.750 0.8966 0.01302 0.00643 -0.0353 0.0481 0.9109
7.000 0.9065 0.01356 0.00692 -0.0325 0.0338 0.9145
7.500 0.9228 0.01489 0.00817 -0.0270 0.0083 0.9227
7.750 0.9369 0.01541 0.00873 -0.0253 0.0074 0.9266
8.000 0.9523 0.01593 0.00929 -0.0240 0.0072 0.9305
8.250 0.9671 0.01650 0.00991 -0.0226 0.0067 0.9348
8.500 0.9828 0.01706 0.01051 -0.0214 0.0064 0.9404
8.750 0.9986 0.01767 0.01117 -0.0203 0.0062 0.9467
9.000 1.0183 0.01831 0.01188 -0.0201 0.0060 0.9542
9.250 1.0421 0.01906 0.01268 -0.0209 0.0058 0.9622
9.500 1.0701 0.01993 0.01361 -0.0228 0.0055 0.9695
9.750 1.0968 0.02094 0.01468 -0.0246 0.0053 0.9838
10.000 1.1066 0.02187 0.01567 -0.0228 0.0052 1.0000
10.250 1.1205 0.02274 0.01657 -0.0218 0.0051 1.0000
10.500 1.1342 0.02363 0.01751 -0.0209 0.0050 1.0000
10.750 1.1467 0.02461 0.01853 -0.0198 0.0050 1.0000
11.000 1.1589 0.02563 0.01960 -0.0187 0.0048 1.0000
11.250 1.1688 0.02681 0.02085 -0.0175 0.0048 1.0000
11.500 1.1806 0.02788 0.02196 -0.0165 0.0047 1.0000
11.750 1.1909 0.02906 0.02321 -0.0155 0.0045 1.0000
12.000 1.2011 0.03027 0.02448 -0.0144 0.0044 1.0000
12.250 1.2100 0.03161 0.02587 -0.0134 0.0043 1.0000
12.500 1.2188 0.03296 0.02728 -0.0124 0.0043 1.0000
12.750 1.2251 0.03455 0.02894 -0.0113 0.0041 1.0000
13.000 1.2312 0.03622 0.03068 -0.0102 0.0041 1.0000
13.250 1.2402 0.03768 0.03219 -0.0095 0.0040 1.0000
13.500 1.2438 0.03969 0.03429 -0.0085 0.0040 1.0000
13.750 1.2485 0.04165 0.03632 -0.0078 0.0039 1.0000
14.000 1.2555 0.04346 0.03821 -0.0072 0.0038 1.0000
14.250 1.2601 0.04554 0.04035 -0.0066 0.0038 1.0000
14.500 1.2639 0.04773 0.04262 -0.0061 0.0037 1.0000
14.750 1.2649 0.05027 0.04526 -0.0056 0.0037 1.0000
15.000 1.2691 0.05256 0.04761 -0.0054 0.0036 1.0000
15.250 1.2693 0.05530 0.05044 -0.0050 0.0036 1.0000
15.500 1.2708 0.05798 0.05319 -0.0049 0.0035 1.0000
15.750 1.2679 0.06119 0.05651 -0.0048 0.0035 1.0000
16.000 1.2661 0.06438 0.05978 -0.0049 0.0034 1.0000
16.250 1.2630 0.06777 0.06328 -0.0050 0.0035 1.0000
16.500 1.2569 0.07157 0.06718 -0.0053 0.0033 1.0000
16.750 1.2543 0.07509 0.07081 -0.0058 0.0034 1.0000
17.000 1.2498 0.07893 0.07475 -0.0064 0.0033 1.0000
17.250 1.2383 0.08368 0.07964 -0.0071 0.0033 1.0000
17.500 1.2405 0.08699 0.08305 -0.0083 0.0032 1.0000
17.750 1.2326 0.09155 0.08773 -0.0095 0.0032 1.0000
18.000 1.2298 0.09568 0.09196 -0.0109 0.0032 1.0000
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Polar data table (+)
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