AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.68 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k132-il-1000000-n5.txt Download as CSV file: xf-ah79k132-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7458 0.03832 0.03508 -0.1118 0.7542 0.0045
-13.500 -0.7743 0.03397 0.03049 -0.1102 0.7532 0.0044
-13.250 -0.7773 0.03204 0.02844 -0.1083 0.7524 0.0045
-13.000 -0.7858 0.02992 0.02615 -0.1054 0.7514 0.0046
-12.750 -0.7851 0.02856 0.02470 -0.1027 0.7506 0.0047
-12.500 -0.7842 0.02735 0.02338 -0.0995 0.7498 0.0048
-12.250 -0.7784 0.02610 0.02199 -0.0971 0.7490 0.0048
-12.000 -0.7692 0.02485 0.02062 -0.0952 0.7480 0.0049
-11.750 -0.7549 0.02395 0.01962 -0.0937 0.7471 0.0051
-11.500 -0.7402 0.02301 0.01857 -0.0923 0.7463 0.0052
-11.250 -0.7231 0.02223 0.01769 -0.0912 0.7454 0.0053
-11.000 -0.7056 0.02142 0.01677 -0.0900 0.7446 0.0055
-10.750 -0.6884 0.02051 0.01574 -0.0889 0.7438 0.0056
-10.500 -0.6682 0.01988 0.01501 -0.0880 0.7430 0.0058
-10.250 -0.6489 0.01909 0.01410 -0.0870 0.7422 0.0060
-10.000 -0.6271 0.01855 0.01346 -0.0864 0.7415 0.0062
-9.750 -0.6062 0.01786 0.01265 -0.0856 0.7406 0.0063
-9.500 -0.5834 0.01738 0.01208 -0.0850 0.7398 0.0065
-9.250 -0.5611 0.01679 0.01139 -0.0844 0.7389 0.0066
-9.000 -0.5380 0.01629 0.01080 -0.0839 0.7381 0.0067
-8.750 -0.5186 0.01523 0.00957 -0.0828 0.7372 0.0070
-8.500 -0.4960 0.01457 0.00882 -0.0821 0.7365 0.0073
-8.250 -0.4723 0.01405 0.00823 -0.0817 0.7356 0.0076
-8.000 -0.4479 0.01360 0.00771 -0.0813 0.7346 0.0078
-7.750 -0.4230 0.01320 0.00727 -0.0809 0.7335 0.0082
-7.500 -0.3979 0.01285 0.00687 -0.0806 0.7325 0.0085
-7.250 -0.3723 0.01253 0.00650 -0.0804 0.7314 0.0091
-7.000 -0.3469 0.01218 0.00610 -0.0801 0.7303 0.0094
-6.750 -0.3214 0.01184 0.00571 -0.0798 0.7292 0.0097
-6.500 -0.2954 0.01156 0.00538 -0.0796 0.7282 0.0100
-6.250 -0.2695 0.01128 0.00504 -0.0794 0.7272 0.0101
-6.000 -0.2443 0.01087 0.00456 -0.0791 0.7261 0.0110
-5.750 -0.2184 0.01058 0.00423 -0.0788 0.7251 0.0118
-5.500 -0.1921 0.01033 0.00395 -0.0787 0.7239 0.0128
-5.250 -0.1657 0.01011 0.00372 -0.0785 0.7227 0.0138
-5.000 -0.1390 0.00990 0.00349 -0.0784 0.7215 0.0148
-4.750 -0.1126 0.00966 0.00327 -0.0783 0.7200 0.0184
-4.500 -0.0859 0.00946 0.00309 -0.0782 0.7183 0.0228
-4.250 -0.0591 0.00927 0.00293 -0.0782 0.7167 0.0285
-4.000 -0.0319 0.00912 0.00277 -0.0781 0.7152 0.0311
-3.750 -0.0048 0.00896 0.00261 -0.0781 0.7137 0.0356
-3.500 0.0225 0.00882 0.00247 -0.0781 0.7122 0.0394
-3.250 0.0499 0.00870 0.00233 -0.0782 0.7108 0.0437
-3.000 0.0772 0.00857 0.00223 -0.0782 0.7093 0.0497
-2.750 0.1047 0.00845 0.00213 -0.0782 0.7075 0.0549
-2.500 0.1321 0.00832 0.00204 -0.0783 0.7054 0.0639
-2.250 0.1598 0.00822 0.00194 -0.0784 0.7031 0.0697
-2.000 0.1873 0.00810 0.00185 -0.0784 0.7009 0.0767
-1.750 0.2149 0.00800 0.00174 -0.0785 0.6987 0.0833
-1.500 0.2423 0.00788 0.00165 -0.0786 0.6965 0.0964
-1.250 0.2695 0.00772 0.00159 -0.0786 0.6940 0.1234
-1.000 0.2965 0.00755 0.00154 -0.0786 0.6910 0.1603
-0.750 0.3231 0.00734 0.00147 -0.0786 0.6878 0.2111
-0.250 0.3662 0.00600 0.00128 -0.0771 0.6818 0.5943
0.000 0.3878 0.00554 0.00128 -0.0759 0.6778 0.7316
0.250 0.4132 0.00543 0.00132 -0.0754 0.6736 0.7848
0.500 0.4395 0.00543 0.00137 -0.0750 0.6694 0.8194
0.750 0.4665 0.00548 0.00147 -0.0748 0.6646 0.8440
1.000 0.4933 0.00556 0.00155 -0.0746 0.6590 0.8588
1.250 0.5207 0.00561 0.00158 -0.0745 0.6536 0.8643
1.500 0.5485 0.00565 0.00161 -0.0746 0.6463 0.8670
1.750 0.5760 0.00570 0.00163 -0.0746 0.6389 0.8697
2.000 0.6033 0.00576 0.00166 -0.0746 0.6297 0.8726
2.250 0.6304 0.00583 0.00169 -0.0746 0.6191 0.8752
2.500 0.6561 0.00594 0.00176 -0.0743 0.6065 0.8790
2.750 0.6818 0.00607 0.00185 -0.0739 0.5935 0.8823
3.000 0.7075 0.00620 0.00193 -0.0737 0.5800 0.8847
3.250 0.7332 0.00634 0.00202 -0.0734 0.5658 0.8865
3.500 0.7584 0.00650 0.00212 -0.0731 0.5497 0.8881
3.750 0.7819 0.00674 0.00227 -0.0724 0.5272 0.8898
4.000 0.8055 0.00694 0.00241 -0.0718 0.5076 0.8915
4.250 0.8286 0.00717 0.00258 -0.0711 0.4883 0.8933
4.500 0.8505 0.00745 0.00277 -0.0701 0.4628 0.8952
4.750 0.8726 0.00773 0.00297 -0.0693 0.4406 0.8968
5.000 0.8943 0.00802 0.00317 -0.0684 0.4185 0.8984
5.250 0.9159 0.00830 0.00338 -0.0674 0.3974 0.9000
5.500 0.9365 0.00863 0.00361 -0.0663 0.3752 0.9017
5.750 0.9555 0.00900 0.00388 -0.0650 0.3489 0.9033
6.000 0.9748 0.00932 0.00414 -0.0636 0.3285 0.9049
6.250 0.9939 0.00963 0.00440 -0.0623 0.3096 0.9065
6.500 1.0080 0.01010 0.00475 -0.0600 0.2796 0.9084
6.750 1.0172 0.01071 0.00518 -0.0569 0.2436 0.9107
7.000 1.0143 0.01148 0.00572 -0.0515 0.1972 0.9141
7.500 1.0075 0.01324 0.00711 -0.0413 0.1199 0.9218
7.750 1.0042 0.01434 0.00805 -0.0370 0.0862 0.9266
8.250 1.0164 0.01627 0.00982 -0.0320 0.0440 0.9353
8.500 1.0301 0.01693 0.01049 -0.0306 0.0372 0.9393
8.750 1.0424 0.01772 0.01125 -0.0291 0.0267 0.9437
9.000 1.0536 0.01875 0.01219 -0.0278 0.0118 0.9494
9.250 1.0721 0.01957 0.01303 -0.0277 0.0076 0.9551
9.500 1.0946 0.02041 0.01391 -0.0284 0.0052 0.9606
9.750 1.1208 0.02126 0.01480 -0.0299 0.0043 0.9651
10.000 1.1462 0.02226 0.01583 -0.0315 0.0034 0.9691
10.500 1.1923 0.02415 0.01782 -0.0335 0.0030 1.0000
10.750 1.2063 0.02514 0.01885 -0.0327 0.0028 1.0000
11.000 1.2194 0.02617 0.01992 -0.0319 0.0026 1.0000
11.250 1.2320 0.02725 0.02106 -0.0311 0.0025 1.0000
11.500 1.2439 0.02838 0.02224 -0.0302 0.0022 1.0000
11.750 1.2545 0.02962 0.02353 -0.0292 0.0021 1.0000
12.000 1.2597 0.03129 0.02529 -0.0278 0.0020 1.0000
12.250 1.2664 0.03287 0.02693 -0.0267 0.0019 1.0000
12.500 1.2787 0.03401 0.02812 -0.0260 0.0019 1.0000
12.750 1.2855 0.03564 0.02983 -0.0250 0.0019 1.0000
13.000 1.2901 0.03756 0.03183 -0.0239 0.0019 1.0000
13.250 1.2996 0.03909 0.03341 -0.0233 0.0019 1.0000
13.500 1.3089 0.04064 0.03502 -0.0227 0.0018 1.0000
13.750 1.3128 0.04274 0.03723 -0.0219 0.0018 1.0000
14.000 1.3195 0.04464 0.03920 -0.0214 0.0018 1.0000
14.250 1.3246 0.04672 0.04135 -0.0208 0.0018 1.0000
14.500 1.3270 0.04910 0.04382 -0.0202 0.0017 1.0000
14.750 1.3284 0.05165 0.04647 -0.0196 0.0017 1.0000
15.000 1.3331 0.05391 0.04880 -0.0193 0.0017 1.0000
15.250 1.3309 0.05695 0.05196 -0.0189 0.0017 1.0000
15.500 1.3314 0.05973 0.05483 -0.0186 0.0017 1.0000
15.750 1.3319 0.06258 0.05776 -0.0185 0.0017 1.0000
16.000 1.3309 0.06567 0.06095 -0.0185 0.0016 1.0000
16.250 1.3302 0.06878 0.06415 -0.0186 0.0016 1.0000
16.500 1.3287 0.07200 0.06746 -0.0187 0.0016 1.0000
16.750 1.3268 0.07534 0.07090 -0.0190 0.0015 1.0000
17.000 1.3225 0.07904 0.07470 -0.0194 0.0015 1.0000
17.250 1.3167 0.08301 0.07878 -0.0199 0.0016 1.0000
17.500 1.3125 0.08683 0.08271 -0.0205 0.0015 1.0000
17.750 1.3060 0.09101 0.08699 -0.0213 0.0015 1.0000
18.000 1.3014 0.09502 0.09110 -0.0222 0.0015 1.0000
18.250 1.2952 0.09934 0.09552 -0.0233 0.0014 1.0000
18.500 1.2803 0.10500 0.10133 -0.0247 0.0015 1.0000
18.750 1.2761 0.10919 0.10560 -0.0261 0.0015 1.0000
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Polar data table (+)
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