AH 80-129 (ah80129-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 100,000 Max Cl/Cd: 39.41 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80129-il-100000-n5.txt Download as CSV file: xf-ah80129-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1040 0.10148 0.09673 -0.0782 0.8695 0.0478
-11.250 -0.1068 0.09876 0.09402 -0.0801 0.8673 0.0493
-10.750 -0.1830 0.10774 0.10260 -0.0829 0.8877 0.0453
-10.500 -0.1795 0.10430 0.09919 -0.0847 0.8839 0.0464
-10.250 -0.1748 0.10119 0.09608 -0.0866 0.8801 0.0469
-10.000 -0.1823 0.09814 0.09309 -0.0916 0.8759 0.0501
-9.750 -0.1825 0.09513 0.09012 -0.0946 0.8718 0.0504
-9.500 -0.1739 0.09098 0.08596 -0.0943 0.8685 0.0497
-9.250 -0.1745 0.08776 0.08278 -0.0971 0.8645 0.0501
-8.750 -0.1735 0.07594 0.07095 -0.1013 0.8573 0.0253
-8.500 -0.1760 0.07232 0.06737 -0.1032 0.8529 0.0248
-8.250 -0.1803 0.06894 0.06396 -0.1047 0.8488 0.0243
-8.000 -0.1897 0.06583 0.06085 -0.1048 0.8439 0.0241
-7.750 -0.1962 0.06298 0.05796 -0.1044 0.8392 0.0236
-7.500 -0.2028 0.05943 0.05430 -0.1039 0.8354 0.0232
-7.250 -0.2054 0.05636 0.05110 -0.1031 0.8313 0.0227
-7.000 -0.2064 0.05331 0.04790 -0.1020 0.8268 0.0223
-6.750 -0.2061 0.04992 0.04427 -0.1004 0.8230 0.0220
-6.500 -0.2036 0.04649 0.04054 -0.0983 0.8198 0.0217
-6.250 -0.1996 0.04369 0.03747 -0.0962 0.8149 0.0213
-6.000 -0.1925 0.04079 0.03420 -0.0939 0.8110 0.0208
-5.750 -0.1827 0.03788 0.03079 -0.0914 0.8081 0.0210
-5.500 -0.1714 0.03554 0.02804 -0.0891 0.8042 0.0209
-5.250 -0.1584 0.03347 0.02555 -0.0868 0.7999 0.0209
-5.000 -0.1410 0.03133 0.02295 -0.0849 0.7967 0.0214
-4.750 -0.1194 0.02978 0.02098 -0.0835 0.7943 0.0238
-4.500 -0.0993 0.02878 0.01962 -0.0821 0.7904 0.0257
-4.250 -0.0794 0.02726 0.01788 -0.0808 0.7863 0.0270
-4.000 -0.0569 0.02596 0.01644 -0.0798 0.7834 0.0286
-3.750 -0.0334 0.02495 0.01532 -0.0789 0.7810 0.0306
-3.500 -0.0136 0.02420 0.01440 -0.0774 0.7776 0.0341
-3.250 0.0027 0.02385 0.01391 -0.0756 0.7726 0.0371
-3.000 0.0229 0.02323 0.01324 -0.0741 0.7695 0.0504
-2.750 0.0447 0.02251 0.01264 -0.0730 0.7671 0.0813
-2.500 0.0606 0.02212 0.01249 -0.0713 0.7627 0.1322
-2.250 0.0746 0.02135 0.01236 -0.0694 0.7580 0.2741
-2.000 0.0900 0.01993 0.01222 -0.0671 0.7552 0.6045
-1.750 0.1860 0.01975 0.01243 -0.0783 0.7559 0.9067
-1.500 0.2880 0.02002 0.01231 -0.0920 0.7564 0.9661
-1.250 0.3593 0.01993 0.01191 -0.1008 0.7554 0.9876
-1.000 0.4130 0.01973 0.01151 -0.1065 0.7538 0.9993
-0.750 0.4323 0.01991 0.01158 -0.1056 0.7496 1.0000
-0.500 0.4470 0.02020 0.01178 -0.1040 0.7443 1.0000
-0.250 0.4666 0.02023 0.01170 -0.1027 0.7411 1.0000
0.000 0.4882 0.02019 0.01156 -0.1018 0.7389 1.0000
0.250 0.4967 0.02079 0.01216 -0.0992 0.7317 1.0000
0.500 0.5156 0.02088 0.01217 -0.0979 0.7282 1.0000
0.750 0.5376 0.02083 0.01204 -0.0969 0.7258 1.0000
1.000 0.5444 0.02149 0.01270 -0.0940 0.7186 1.0000
1.250 0.5630 0.02160 0.01276 -0.0925 0.7149 1.0000
1.500 0.5855 0.02157 0.01268 -0.0916 0.7126 1.0000
1.750 0.5900 0.02228 0.01342 -0.0883 0.7050 1.0000
2.000 0.6093 0.02238 0.01349 -0.0869 0.7013 1.0000
2.250 0.6335 0.02231 0.01339 -0.0861 0.6990 1.0000
2.500 0.6356 0.02312 0.01421 -0.0824 0.6907 1.0000
2.750 0.6569 0.02318 0.01427 -0.0813 0.6874 1.0000
3.000 0.6828 0.02306 0.01415 -0.0808 0.6853 1.0000
3.250 0.6821 0.02403 0.01515 -0.0767 0.6764 1.0000
3.500 0.7062 0.02400 0.01517 -0.0760 0.6734 1.0000
3.750 0.7342 0.02382 0.01502 -0.0759 0.6715 1.0000
4.000 0.7317 0.02489 0.01612 -0.0716 0.6617 1.0000
4.250 0.7589 0.02474 0.01602 -0.0713 0.6592 1.0000
4.500 0.7877 0.02455 0.01589 -0.0712 0.6571 1.0000
4.750 0.7848 0.02565 0.01703 -0.0669 0.6470 1.0000
5.000 0.8149 0.02537 0.01690 -0.0670 0.6448 1.0000
5.500 0.8397 0.02637 0.01806 -0.0626 0.6322 1.0000
5.750 0.8692 0.02615 0.01796 -0.0626 0.6296 1.0000
6.250 0.8685 0.02831 0.02032 -0.0552 0.6103 1.0000
6.500 0.8932 0.02826 0.02043 -0.0546 0.6061 1.0000
6.750 0.9270 0.02771 0.02007 -0.0549 0.6038 1.0000
7.250 0.9608 0.02838 0.02107 -0.0519 0.5903 1.0000
7.750 0.9973 0.02860 0.02166 -0.0489 0.5736 1.0000
8.250 1.0255 0.02602 0.01899 -0.0414 0.4772 1.0000
8.500 1.0221 0.02668 0.01873 -0.0363 0.3483 1.0000
8.750 0.9986 0.02964 0.02084 -0.0311 0.2373 1.0000
9.000 0.9785 0.03287 0.02333 -0.0271 0.1395 1.0000
9.250 0.9577 0.03645 0.02606 -0.0232 0.0441 1.0000
9.500 0.9575 0.03859 0.02809 -0.0210 0.0286 1.0000
9.750 0.9611 0.04050 0.03008 -0.0192 0.0248 1.0000
10.000 0.9677 0.04216 0.03191 -0.0177 0.0229 1.0000
10.250 0.9706 0.04416 0.03400 -0.0162 0.0185 1.0000
10.500 0.9757 0.04606 0.03606 -0.0148 0.0184 1.0000
10.750 0.9748 0.04854 0.03864 -0.0131 0.0165 1.0000
11.000 0.9813 0.05036 0.04061 -0.0119 0.0157 1.0000
11.250 0.9872 0.05230 0.04269 -0.0104 0.0151 1.0000
11.500 0.9958 0.05404 0.04462 -0.0090 0.0144 1.0000
11.750 1.0083 0.05559 0.04627 -0.0074 0.0135 1.0000
12.000 1.0248 0.05695 0.04777 -0.0059 0.0131 1.0000
12.250 1.0447 0.05843 0.04940 -0.0046 0.0127 1.0000
12.500 1.0655 0.06026 0.05143 -0.0033 0.0125 1.0000
12.750 1.0818 0.06265 0.05407 -0.0022 0.0122 1.0000
13.000 1.0924 0.06520 0.05689 -0.0012 0.0122 1.0000
13.250 1.0979 0.06825 0.06023 -0.0002 0.0123 1.0000
13.500 1.0974 0.07179 0.06407 0.0008 0.0122 1.0000
13.750 1.0931 0.07551 0.06808 0.0016 0.0122 1.0000
14.000 1.0862 0.07939 0.07224 0.0021 0.0123 1.0000
14.250 1.0755 0.08374 0.07685 0.0023 0.0121 1.0000
14.500 1.0626 0.08858 0.08199 0.0021 0.0125 1.0000
14.750 1.0468 0.09395 0.08761 0.0014 0.0125 1.0000
15.000 1.0329 0.09903 0.09288 0.0002 0.0119 1.0000
15.250 1.0137 0.10564 0.09977 -0.0018 0.0127 1.0000
15.500 0.9963 0.11215 0.10649 -0.0044 0.0127 1.0000
15.750 0.9805 0.11879 0.11331 -0.0075 0.0129 1.0000
16.000 0.9587 0.12735 0.12207 -0.0120 0.0130 1.0000
16.250 0.9391 0.13627 0.13113 -0.0171 0.0130 1.0000
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Polar data table (+)
Polar graphs
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