AH 80-129 (ah80129-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 500,000 Max Cl/Cd: 124.73 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80129-il-500000.txt Download as CSV file: xf-ah80129-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-129
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1668 0.08366 0.08067 -0.0914 0.8098 0.0166
-9.250 -0.1596 0.08059 0.07758 -0.0931 0.8079 0.0165
-9.000 -0.1563 0.07645 0.07346 -0.0963 0.8057 0.0165
-8.750 -0.1539 0.07266 0.06970 -0.0988 0.8030 0.0165
-8.500 -0.1549 0.06791 0.06499 -0.1033 0.8000 0.0166
-8.250 -0.1594 0.06347 0.06051 -0.1069 0.7971 0.0165
-8.000 -0.1660 0.06000 0.05698 -0.1071 0.7944 0.0165
-7.750 -0.1717 0.05723 0.05416 -0.1060 0.7917 0.0165
-7.500 -0.2100 0.04908 0.04587 -0.1037 0.7880 0.0172
-7.250 -0.2077 0.04626 0.04292 -0.1020 0.7853 0.0172
-7.000 -0.2111 0.04280 0.03931 -0.1000 0.7827 0.0176
-6.750 -0.2045 0.04106 0.03749 -0.0986 0.7807 0.0186
-6.500 -0.1952 0.03947 0.03581 -0.0971 0.7784 0.0203
-6.250 -0.1874 0.03668 0.03286 -0.0950 0.7754 0.0206
-6.000 -0.1768 0.03418 0.03013 -0.0930 0.7726 0.0220
-5.750 -0.1510 0.03422 0.02987 -0.0912 0.7703 0.0260
-5.500 -0.1376 0.03220 0.02756 -0.0891 0.7680 0.0261
-5.250 -0.1406 0.02633 0.02130 -0.0857 0.7660 0.0287
-5.000 -0.1219 0.02521 0.02014 -0.0847 0.7633 0.0308
-4.750 -0.1048 0.01976 0.01381 -0.0799 0.7606 0.0171
-4.500 -0.0829 0.01755 0.01137 -0.0787 0.7582 0.0156
-4.250 -0.0592 0.01574 0.00931 -0.0777 0.7559 0.0150
-4.000 -0.0347 0.01447 0.00786 -0.0768 0.7540 0.0150
-3.750 -0.0109 0.01357 0.00681 -0.0760 0.7522 0.0150
-3.500 0.0122 0.01305 0.00621 -0.0750 0.7492 0.0164
-3.250 0.0346 0.01248 0.00557 -0.0740 0.7464 0.0164
-3.000 0.0558 0.01174 0.00472 -0.0725 0.7439 0.0195
-2.750 0.0810 0.01146 0.00440 -0.0721 0.7417 0.0237
-2.500 0.1055 0.01104 0.00396 -0.0713 0.7396 0.0396
-2.250 0.1274 0.01059 0.00376 -0.0703 0.7370 0.1084
-2.000 0.1474 0.01006 0.00363 -0.0691 0.7338 0.2171
-1.750 0.1626 0.00925 0.00349 -0.0671 0.7309 0.4166
-1.500 0.1695 0.00830 0.00336 -0.0629 0.7283 0.6569
-1.250 0.1897 0.00778 0.00348 -0.0607 0.7263 0.8624
-1.000 0.2250 0.00780 0.00351 -0.0621 0.7240 0.9026
-0.750 0.2607 0.00785 0.00353 -0.0638 0.7208 0.9221
-0.500 0.2997 0.00792 0.00354 -0.0662 0.7181 0.9374
-0.250 0.3519 0.00808 0.00363 -0.0712 0.7158 0.9521
0.000 0.4038 0.00825 0.00369 -0.0763 0.7137 0.9593
0.250 0.4503 0.00838 0.00373 -0.0803 0.7116 0.9647
0.500 0.4907 0.00848 0.00383 -0.0831 0.7083 0.9709
0.750 0.5360 0.00854 0.00386 -0.0871 0.7051 0.9749
1.000 0.5725 0.00857 0.00384 -0.0892 0.7021 0.9797
1.250 0.6100 0.00855 0.00377 -0.0915 0.6994 0.9828
1.500 0.6466 0.00856 0.00377 -0.0938 0.6965 0.9852
1.750 0.6806 0.00855 0.00379 -0.0955 0.6927 0.9885
2.000 0.7150 0.00853 0.00375 -0.0973 0.6893 0.9912
2.250 0.7508 0.00846 0.00365 -0.0993 0.6859 0.9933
2.500 0.7847 0.00844 0.00367 -0.1010 0.6819 0.9959
2.750 0.8185 0.00840 0.00366 -0.1028 0.6775 0.9982
3.000 0.8525 0.00835 0.00361 -0.1045 0.6738 1.0000
3.250 0.8755 0.00836 0.00362 -0.1038 0.6702 1.0000
3.500 0.8963 0.00839 0.00373 -0.1027 0.6654 1.0000
3.750 0.9185 0.00839 0.00376 -0.1019 0.6609 1.0000
4.000 0.9416 0.00841 0.00377 -0.1012 0.6569 1.0000
4.250 0.9621 0.00844 0.00389 -0.1000 0.6513 1.0000
4.500 0.9843 0.00846 0.00394 -0.0992 0.6466 1.0000
4.750 1.0066 0.00852 0.00403 -0.0983 0.6421 1.0000
5.000 1.0272 0.00856 0.00417 -0.0972 0.6357 1.0000
5.250 1.0475 0.00856 0.00420 -0.0958 0.6262 1.0000
5.500 1.0602 0.00850 0.00405 -0.0927 0.5934 1.0000
5.750 1.0732 0.00869 0.00414 -0.0899 0.5624 1.0000
6.000 1.0783 0.00920 0.00441 -0.0857 0.5079 1.0000
6.250 1.0854 0.00974 0.00479 -0.0820 0.4674 1.0000
6.500 1.0837 0.01059 0.00537 -0.0767 0.4116 1.0000
6.750 1.0650 0.01204 0.00634 -0.0687 0.3290 1.0000
7.000 1.0495 0.01325 0.00724 -0.0615 0.2715 1.0000
7.250 1.0214 0.01570 0.00912 -0.0539 0.1698 1.0000
7.500 0.9942 0.01883 0.01153 -0.0477 0.0492 1.0000
7.750 0.9868 0.02107 0.01360 -0.0438 0.0111 1.0000
8.000 0.9985 0.02211 0.01477 -0.0422 0.0108 1.0000
8.250 1.0057 0.02347 0.01624 -0.0402 0.0097 1.0000
8.500 1.0161 0.02464 0.01749 -0.0387 0.0092 1.0000
8.750 1.0187 0.02642 0.01939 -0.0363 0.0092 1.0000
9.000 1.0249 0.02795 0.02100 -0.0344 0.0091 1.0000
9.250 1.0343 0.02926 0.02238 -0.0330 0.0083 1.0000
9.500 1.0429 0.03064 0.02382 -0.0315 0.0078 1.0000
9.750 1.0494 0.03222 0.02548 -0.0299 0.0077 1.0000
10.000 1.0567 0.03375 0.02708 -0.0283 0.0077 1.0000
10.250 1.0635 0.03536 0.02877 -0.0265 0.0074 1.0000
10.500 1.0713 0.03690 0.03033 -0.0253 0.0062 1.0000
10.750 0.9217 0.02207 0.01623 -0.0097 0.0062 1.0000
11.000 0.9293 0.02408 0.01832 -0.0084 0.0065 1.0000
11.250 0.9350 0.02660 0.02092 -0.0065 0.0062 1.0000
11.500 0.9472 0.02851 0.02294 -0.0049 0.0066 1.0000
11.750 0.9601 0.03066 0.02517 -0.0031 0.0064 1.0000
12.000 1.2130 0.05245 0.04749 -0.0144 0.0135 1.0000
12.250 1.2089 0.05514 0.05036 -0.0123 0.0131 1.0000
12.500 1.2020 0.05790 0.05329 -0.0103 0.0125 1.0000
12.750 1.1934 0.06098 0.05654 -0.0085 0.0121 1.0000
13.000 1.1855 0.06400 0.05974 -0.0069 0.0122 1.0000
13.250 1.1761 0.06715 0.06302 -0.0057 0.0119 1.0000
13.500 1.1634 0.07087 0.06691 -0.0045 0.0118 1.0000
13.750 1.1494 0.07475 0.07096 -0.0037 0.0118 1.0000
14.000 1.1365 0.07864 0.07499 -0.0033 0.0116 1.0000
14.250 1.1211 0.08306 0.07955 -0.0032 0.0115 1.0000
14.500 1.1003 0.08841 0.08511 -0.0037 0.0117 1.0000
14.750 1.0829 0.09368 0.09051 -0.0046 0.0115 1.0000
15.000 1.0690 0.09883 0.09575 -0.0059 0.0113 1.0000
15.250 1.0458 0.10578 0.10292 -0.0085 0.0115 1.0000
15.500 1.0236 0.11332 0.11062 -0.0117 0.0116 1.0000
15.750 1.0021 0.12146 0.11892 -0.0158 0.0118 1.0000
16.000 0.9838 0.12942 0.12698 -0.0202 0.0116 1.0000
16.250 0.9546 0.14170 0.13942 -0.0275 0.0118 1.0000
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