AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 500,000 Max Cl/Cd: 107.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150a-il-500000-n5.txt Download as CSV file: xf-ah82150a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5723 0.04752 0.04439 -0.1210 0.8878 0.0085
-13.250 -0.6025 0.04118 0.03768 -0.1239 0.8689 0.0082
-12.750 -0.6276 0.03475 0.03072 -0.1231 0.8452 0.0085
-12.500 -0.6339 0.03238 0.02812 -0.1217 0.8364 0.0085
-12.250 -0.6377 0.03029 0.02578 -0.1200 0.8284 0.0087
-12.000 -0.6368 0.02861 0.02388 -0.1184 0.8215 0.0088
-11.750 -0.6352 0.02696 0.02200 -0.1164 0.8151 0.0090
-11.500 -0.6289 0.02571 0.02054 -0.1146 0.8100 0.0091
-11.250 -0.6224 0.02447 0.01912 -0.1127 0.8048 0.0093
-11.000 -0.6172 0.02323 0.01770 -0.1103 0.8000 0.0095
-10.750 -0.6099 0.02223 0.01655 -0.1080 0.7957 0.0097
-10.500 -0.5960 0.02140 0.01561 -0.1066 0.7914 0.0100
-10.250 -0.5790 0.02076 0.01488 -0.1055 0.7874 0.0103
-10.000 -0.5607 0.02017 0.01418 -0.1046 0.7841 0.0108
-9.750 -0.5419 0.01951 0.01341 -0.1037 0.7810 0.0111
-9.500 -0.5223 0.01886 0.01264 -0.1029 0.7777 0.0116
-9.250 -0.5018 0.01827 0.01195 -0.1022 0.7743 0.0122
-9.000 -0.4805 0.01775 0.01130 -0.1016 0.7711 0.0128
-8.500 -0.4385 0.01658 0.00998 -0.1003 0.7655 0.0142
-8.250 -0.4155 0.01618 0.00954 -0.0999 0.7626 0.0150
-8.000 -0.3925 0.01577 0.00906 -0.0994 0.7597 0.0158
-7.750 -0.3694 0.01535 0.00854 -0.0990 0.7570 0.0167
-7.500 -0.3456 0.01499 0.00808 -0.0986 0.7545 0.0175
-7.250 -0.3231 0.01447 0.00752 -0.0981 0.7518 0.0186
-7.000 -0.2986 0.01418 0.00722 -0.0979 0.7491 0.0200
-6.750 -0.2738 0.01390 0.00691 -0.0977 0.7465 0.0215
-6.500 -0.2488 0.01364 0.00659 -0.0975 0.7439 0.0230
-6.250 -0.2238 0.01337 0.00623 -0.0973 0.7414 0.0239
-5.750 -0.1746 0.01269 0.00552 -0.0968 0.7367 0.0280
-5.500 -0.1491 0.01243 0.00522 -0.0967 0.7342 0.0298
-5.250 -0.1233 0.01220 0.00494 -0.0966 0.7315 0.0314
-5.000 -0.0978 0.01192 0.00462 -0.0965 0.7290 0.0336
-4.750 -0.0720 0.01165 0.00433 -0.0965 0.7268 0.0365
-4.250 -0.0189 0.01128 0.00388 -0.0965 0.7223 0.0420
-4.000 0.0074 0.01104 0.00366 -0.0966 0.7197 0.0472
-3.750 0.0342 0.01086 0.00347 -0.0967 0.7171 0.0530
-3.500 0.0610 0.01066 0.00329 -0.0968 0.7148 0.0624
-3.250 0.0879 0.01046 0.00312 -0.0969 0.7126 0.0797
-3.000 0.1143 0.01017 0.00295 -0.0971 0.7105 0.1185
-2.750 0.1404 0.00979 0.00280 -0.0973 0.7080 0.1819
-2.500 0.1667 0.00939 0.00265 -0.0976 0.7055 0.2563
-2.250 0.1925 0.00878 0.00245 -0.0980 0.7029 0.3783
-2.000 0.2167 0.00779 0.00235 -0.0983 0.7004 0.6258
-1.750 0.2449 0.00785 0.00245 -0.0984 0.6981 0.6710
-1.250 0.3011 0.00820 0.00281 -0.0984 0.6934 0.7219
-1.000 0.3293 0.00831 0.00291 -0.0985 0.6906 0.7312
-0.750 0.3574 0.00841 0.00299 -0.0986 0.6877 0.7377
-0.500 0.3860 0.00848 0.00301 -0.0989 0.6850 0.7435
-0.250 0.4144 0.00852 0.00301 -0.0991 0.6824 0.7456
0.000 0.4428 0.00852 0.00301 -0.0994 0.6790 0.7468
0.250 0.4711 0.00852 0.00300 -0.0997 0.6751 0.7479
0.500 0.4996 0.00853 0.00297 -0.1001 0.6711 0.7489
0.750 0.5281 0.00855 0.00294 -0.1004 0.6676 0.7499
1.000 0.5564 0.00855 0.00296 -0.1007 0.6636 0.7511
1.250 0.5847 0.00857 0.00297 -0.1010 0.6595 0.7524
1.500 0.6131 0.00860 0.00298 -0.1014 0.6559 0.7536
1.750 0.6416 0.00863 0.00298 -0.1017 0.6526 0.7547
2.000 0.6698 0.00865 0.00302 -0.1021 0.6483 0.7557
2.250 0.6980 0.00868 0.00306 -0.1024 0.6439 0.7567
2.500 0.7260 0.00872 0.00308 -0.1026 0.6399 0.7575
2.750 0.7537 0.00875 0.00314 -0.1028 0.6352 0.7585
3.000 0.7812 0.00878 0.00321 -0.1030 0.6302 0.7595
3.250 0.8086 0.00883 0.00328 -0.1031 0.6254 0.7605
3.500 0.8361 0.00888 0.00337 -0.1033 0.6200 0.7615
3.750 0.8632 0.00894 0.00345 -0.1034 0.6143 0.7625
4.000 0.8902 0.00900 0.00354 -0.1035 0.6086 0.7635
4.250 0.9171 0.00907 0.00365 -0.1035 0.6017 0.7646
4.500 0.9435 0.00915 0.00375 -0.1035 0.5945 0.7657
4.750 0.9697 0.00924 0.00387 -0.1034 0.5857 0.7669
5.000 0.9955 0.00934 0.00401 -0.1032 0.5762 0.7681
5.250 1.0194 0.00949 0.00414 -0.1027 0.5602 0.7694
5.500 1.0396 0.00975 0.00430 -0.1014 0.5327 0.7709
5.750 1.0536 0.01023 0.00458 -0.0991 0.4888 0.7723
6.000 1.0605 0.01096 0.00504 -0.0954 0.4342 0.7737
6.250 1.0637 0.01181 0.00562 -0.0913 0.3809 0.7751
6.500 1.0634 0.01260 0.00618 -0.0864 0.3337 0.7767
6.750 1.0628 0.01352 0.00686 -0.0818 0.2866 0.7785
7.000 1.0602 0.01462 0.00771 -0.0771 0.2365 0.7805
7.250 1.0578 0.01585 0.00869 -0.0729 0.1868 0.7825
7.500 1.0539 0.01729 0.00985 -0.0687 0.1354 0.7845
7.750 1.0504 0.01886 0.01116 -0.0649 0.0858 0.7864
8.000 1.0478 0.02048 0.01255 -0.0615 0.0408 0.7882
8.250 1.0511 0.02187 0.01382 -0.0589 0.0179 0.7901
8.500 1.0636 0.02275 0.01475 -0.0574 0.0144 0.7920
8.750 1.0751 0.02372 0.01575 -0.0559 0.0122 0.7940
9.000 1.0889 0.02456 0.01667 -0.0547 0.0114 0.7959
9.250 1.1017 0.02550 0.01767 -0.0535 0.0106 0.7980
9.500 1.1140 0.02650 0.01872 -0.0522 0.0100 0.7999
9.750 1.1250 0.02760 0.01988 -0.0509 0.0094 0.8018
10.000 1.1342 0.02884 0.02122 -0.0495 0.0089 0.8037
10.250 1.1426 0.03018 0.02264 -0.0480 0.0084 0.8059
10.500 1.1537 0.03134 0.02388 -0.0469 0.0082 0.8082
10.750 1.1636 0.03263 0.02525 -0.0458 0.0078 0.8106
11.000 1.1731 0.03398 0.02667 -0.0447 0.0075 0.8131
11.500 1.1913 0.03684 0.02967 -0.0427 0.0068 0.8183
11.750 1.1987 0.03846 0.03138 -0.0416 0.0066 0.8213
12.000 1.2054 0.04020 0.03322 -0.0407 0.0064 0.8247
12.250 1.2108 0.04213 0.03523 -0.0397 0.0062 0.8281
12.500 1.2135 0.04436 0.03755 -0.0387 0.0060 0.8314
12.750 1.2144 0.04682 0.04012 -0.0377 0.0058 0.8349
13.000 1.2204 0.04885 0.04225 -0.0370 0.0058 0.8390
13.250 1.2272 0.05085 0.04436 -0.0365 0.0056 0.8434
13.500 1.2318 0.05311 0.04673 -0.0359 0.0055 0.8481
13.750 1.2368 0.05537 0.04911 -0.0355 0.0054 0.8537
14.250 1.2454 0.06016 0.05415 -0.0347 0.0052 0.8678
14.500 1.2488 0.06267 0.05680 -0.0343 0.0051 0.8780
14.750 1.2525 0.06511 0.05941 -0.0339 0.0049 0.8953
15.000 1.2550 0.06759 0.06209 -0.0337 0.0049 0.9906
15.250 1.2589 0.07032 0.06492 -0.0338 0.0048 1.0000
15.500 1.2621 0.07326 0.06796 -0.0340 0.0046 1.0000
15.750 1.2655 0.07622 0.07102 -0.0344 0.0045 1.0000
16.000 1.2689 0.07924 0.07414 -0.0350 0.0044 1.0000
16.250 1.2711 0.08248 0.07747 -0.0357 0.0043 1.0000
16.500 1.2724 0.08590 0.08100 -0.0364 0.0043 1.0000
16.750 1.2737 0.08941 0.08459 -0.0375 0.0042 1.0000
17.000 1.2739 0.09313 0.08841 -0.0385 0.0041 1.0000
17.250 1.2730 0.09703 0.09242 -0.0398 0.0040 1.0000
17.500 1.2708 0.10124 0.09674 -0.0412 0.0039 1.0000
17.750 1.2664 0.10582 0.10146 -0.0427 0.0039 1.0000
18.000 1.2592 0.11096 0.10679 -0.0445 0.0038 1.0000
18.250 1.2552 0.11576 0.11173 -0.0466 0.0038 1.0000
18.500 1.2503 0.12078 0.11690 -0.0489 0.0037 1.0000
18.750 1.2444 0.12606 0.12234 -0.0515 0.0037 1.0000
19.000 1.2378 0.13160 0.12803 -0.0544 0.0037 1.0000
19.250 1.2302 0.13744 0.13403 -0.0576 0.0037 1.0000
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Polar data table (+)
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