AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 500,000 Max Cl/Cd: 104.27 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k135-il-500000.txt Download as CSV file: xf-ah79k135-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3558 0.05100 0.04740 -0.0962 0.7940 0.0243
-8.250 -0.3841 0.04467 0.04082 -0.0927 0.7924 0.0249
-8.000 -0.3761 0.04227 0.03838 -0.0915 0.7912 0.0254
-7.750 -0.3658 0.04057 0.03661 -0.0903 0.7898 0.0259
-6.500 -0.3198 0.02302 0.01718 -0.0776 0.7820 0.0170
-6.250 -0.2989 0.01977 0.01336 -0.0759 0.7804 0.0146
-6.000 -0.2745 0.01882 0.01224 -0.0752 0.7789 0.0143
-5.750 -0.2505 0.01790 0.01121 -0.0746 0.7776 0.0143
-5.500 -0.2272 0.01699 0.01021 -0.0738 0.7763 0.0143
-5.250 -0.2052 0.01613 0.00927 -0.0728 0.7750 0.0146
-5.000 -0.1832 0.01549 0.00860 -0.0719 0.7734 0.0150
-4.750 -0.1603 0.01495 0.00805 -0.0712 0.7713 0.0158
-4.500 -0.1365 0.01452 0.00759 -0.0706 0.7691 0.0168
-4.250 -0.1120 0.01416 0.00717 -0.0700 0.7672 0.0183
-4.000 -0.0878 0.01371 0.00668 -0.0694 0.7654 0.0212
-3.750 -0.0633 0.01329 0.00634 -0.0688 0.7638 0.0351
-3.500 -0.0390 0.01289 0.00607 -0.0683 0.7623 0.0732
-3.250 -0.0139 0.01261 0.00589 -0.0680 0.7610 0.1065
-3.000 0.0089 0.01218 0.00576 -0.0675 0.7589 0.1771
-2.750 0.0273 0.01134 0.00558 -0.0664 0.7560 0.3444
-2.500 0.0412 0.01021 0.00538 -0.0643 0.7534 0.5845
-2.250 0.0610 0.00974 0.00539 -0.0625 0.7513 0.7186
-2.000 0.0865 0.00966 0.00539 -0.0618 0.7496 0.7702
-1.750 0.1132 0.00966 0.00539 -0.0613 0.7481 0.7983
-1.500 0.1402 0.00972 0.00542 -0.0609 0.7467 0.8190
-1.250 0.1659 0.00983 0.00552 -0.0604 0.7439 0.8333
-1.000 0.1917 0.00992 0.00560 -0.0598 0.7407 0.8464
-0.750 0.2175 0.01002 0.00567 -0.0591 0.7382 0.8585
-0.500 0.2437 0.01006 0.00569 -0.0584 0.7361 0.8675
-0.250 0.2691 0.01012 0.00573 -0.0574 0.7343 0.8791
0.000 0.2939 0.01020 0.00576 -0.0563 0.7327 0.8910
0.250 0.3168 0.01028 0.00586 -0.0549 0.7297 0.8981
0.500 0.3410 0.01028 0.00587 -0.0541 0.7259 0.9055
0.750 0.3665 0.01020 0.00578 -0.0533 0.7232 0.9101
1.000 0.3936 0.01008 0.00563 -0.0531 0.7210 0.9152
1.250 0.4217 0.00994 0.00545 -0.0532 0.7191 0.9194
1.500 0.4477 0.00984 0.00535 -0.0527 0.7162 0.9228
1.750 0.4723 0.00978 0.00531 -0.0520 0.7117 0.9273
2.000 0.4992 0.00964 0.00516 -0.0519 0.7083 0.9315
2.250 0.5274 0.00945 0.00495 -0.0520 0.7056 0.9344
2.500 0.5555 0.00930 0.00480 -0.0520 0.7026 0.9371
2.750 0.5803 0.00921 0.00476 -0.0515 0.6971 0.9406
3.000 0.6076 0.00904 0.00459 -0.0515 0.6929 0.9441
3.250 0.6354 0.00887 0.00439 -0.0515 0.6891 0.9472
3.500 0.6613 0.00874 0.00433 -0.0512 0.6817 0.9500
3.750 0.6900 0.00856 0.00414 -0.0514 0.6765 0.9528
4.000 0.7152 0.00849 0.00413 -0.0510 0.6689 0.9565
4.250 0.7408 0.00837 0.00400 -0.0506 0.6623 0.9599
4.500 0.7693 0.00829 0.00398 -0.0509 0.6520 0.9625
4.750 0.7982 0.00821 0.00390 -0.0513 0.6386 0.9651
5.000 0.8256 0.00818 0.00383 -0.0513 0.6217 0.9681
5.250 0.8492 0.00823 0.00383 -0.0506 0.5995 0.9721
5.500 0.8759 0.00840 0.00389 -0.0507 0.5707 0.9748
5.750 0.9037 0.00868 0.00407 -0.0512 0.5389 0.9774
6.000 0.9299 0.00905 0.00432 -0.0514 0.5055 0.9806
6.250 0.9535 0.00947 0.00462 -0.0512 0.4717 0.9846
6.500 0.9819 0.00999 0.00501 -0.0522 0.4333 0.9866
6.750 1.0051 0.01080 0.00556 -0.0524 0.3772 0.9899
7.000 1.0220 0.01191 0.00631 -0.0518 0.3060 0.9960
7.250 1.0134 0.01276 0.00689 -0.0460 0.2542 1.0000
7.500 1.0007 0.01339 0.00735 -0.0391 0.2210 1.0000
7.750 0.9935 0.01469 0.00831 -0.0344 0.1629 1.0000
8.000 0.9906 0.01623 0.00954 -0.0311 0.1093 1.0000
8.250 0.9807 0.01843 0.01129 -0.0274 0.0396 1.0000
8.500 0.9862 0.01977 0.01247 -0.0252 0.0193 1.0000
8.750 0.9995 0.02063 0.01339 -0.0240 0.0169 1.0000
9.000 1.0117 0.02158 0.01439 -0.0226 0.0154 1.0000
9.250 1.0221 0.02265 0.01553 -0.0210 0.0146 1.0000
9.500 1.0332 0.02369 0.01664 -0.0196 0.0141 1.0000
9.750 1.0442 0.02476 0.01777 -0.0182 0.0137 1.0000
10.000 1.0545 0.02588 0.01896 -0.0169 0.0133 1.0000
10.250 1.0632 0.02713 0.02028 -0.0154 0.0130 1.0000
10.500 1.0713 0.02845 0.02168 -0.0139 0.0127 1.0000
10.750 1.0782 0.02988 0.02318 -0.0124 0.0124 1.0000
11.000 1.0839 0.03143 0.02480 -0.0109 0.0121 1.0000
11.250 1.0899 0.03299 0.02644 -0.0095 0.0121 1.0000
11.500 1.0954 0.03463 0.02814 -0.0081 0.0118 1.0000
11.750 1.1006 0.03634 0.02992 -0.0068 0.0116 1.0000
12.000 1.1063 0.03805 0.03169 -0.0056 0.0114 1.0000
12.250 1.1125 0.03976 0.03346 -0.0044 0.0113 1.0000
12.500 1.1167 0.04172 0.03546 -0.0032 0.0108 1.0000
12.750 1.1254 0.04337 0.03719 -0.0021 0.0109 1.0000
13.000 1.1351 0.04503 0.03891 -0.0009 0.0107 1.0000
13.250 1.1495 0.04660 0.04056 0.0003 0.0106 1.0000
13.500 1.1626 0.04815 0.04220 0.0011 0.0106 1.0000
13.750 1.1769 0.04984 0.04400 0.0019 0.0106 1.0000
14.000 1.1924 0.05194 0.04624 0.0027 0.0106 1.0000
14.250 1.2019 0.05419 0.04864 0.0035 0.0106 1.0000
14.500 1.2075 0.05666 0.05127 0.0042 0.0106 1.0000
14.750 1.2081 0.05888 0.05364 0.0047 0.0108 1.0000
15.000 1.2080 0.06184 0.05679 0.0052 0.0108 1.0000
15.250 1.1758 0.07017 0.06591 0.0067 0.0129 1.0000
15.500 1.0621 0.07178 0.06764 0.0049 0.0110 1.0000
15.750 1.0288 0.07995 0.07632 0.0034 0.0119 1.0000
16.000 0.9923 0.08695 0.08367 0.0009 0.0125 1.0000
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Polar data table (+)
Polar graphs
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