AH 80-129 (ah80129-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 200,000 Max Cl/Cd: 78.98 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80129-il-200000.txt Download as CSV file: xf-ah80129-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1553 0.10285 0.09915 -0.0922 0.9029 0.0353
-10.500 -0.1571 0.09997 0.09631 -0.0971 0.8990 0.0373
-10.250 -0.1540 0.09708 0.09343 -0.0996 0.8948 0.0375
-10.000 -0.0776 0.07721 0.07379 -0.0897 0.8724 0.0428
-9.750 -0.0758 0.07410 0.07070 -0.0906 0.8696 0.0439
-9.500 -0.1382 0.08595 0.08231 -0.1008 0.8856 0.0423
-9.250 -0.1555 0.08128 0.07773 -0.1080 0.8797 0.0387
-9.000 -0.1399 0.07926 0.07567 -0.1046 0.8774 0.0409
-8.750 -0.1412 0.07603 0.07245 -0.1062 0.8738 0.0409
-8.500 -0.1406 0.07340 0.06983 -0.1066 0.8698 0.0422
-8.250 -0.1435 0.07059 0.06704 -0.1078 0.8654 0.0436
-8.000 -0.1550 0.06722 0.06366 -0.1094 0.8611 0.0430
-7.750 -0.1671 0.06475 0.06121 -0.1089 0.8557 0.0425
-7.500 -0.1813 0.06238 0.05869 -0.1093 0.8505 0.0498
-7.250 -0.1817 0.05947 0.05567 -0.1082 0.8475 0.0496
-7.000 -0.1875 0.05833 0.05423 -0.1066 0.8418 0.0506
-6.750 -0.1896 0.05280 0.04871 -0.1058 0.8384 0.0528
-6.500 -0.1794 0.05051 0.04643 -0.1045 0.8357 0.0551
-6.250 -0.1722 0.04836 0.04415 -0.1031 0.8321 0.0571
-6.000 -0.1649 0.04623 0.04183 -0.1015 0.8273 0.0603
-5.750 -0.1511 0.02098 0.01676 -0.0932 0.8118 0.0665
-5.500 -0.1388 0.01874 0.01447 -0.0918 0.8090 0.0686
-5.250 -0.1273 0.01657 0.01212 -0.0899 0.8068 0.0722
-4.750 -0.1108 0.03038 0.02396 -0.0877 0.8093 0.0346
-4.500 -0.0914 0.02757 0.02067 -0.0855 0.8073 0.0314
-4.250 -0.0751 0.02582 0.01852 -0.0833 0.8017 0.0299
-4.000 -0.0523 0.02437 0.01681 -0.0821 0.7982 0.0302
-3.750 -0.0266 0.02307 0.01532 -0.0813 0.7959 0.0307
-3.500 -0.0001 0.02256 0.01462 -0.0806 0.7940 0.0367
-3.250 0.0172 0.02218 0.01419 -0.0792 0.7886 0.0372
-3.000 0.0353 0.02110 0.01310 -0.0773 0.7846 0.0410
-2.750 0.0572 0.02043 0.01238 -0.0759 0.7821 0.0483
-2.500 0.0767 0.01934 0.01144 -0.0739 0.7803 0.0965
-2.250 0.0821 0.01918 0.01179 -0.0708 0.7731 0.1992
-2.000 0.0799 0.01771 0.01172 -0.0653 0.7692 0.5407
-1.750 0.1802 0.01712 0.01206 -0.0773 0.7703 0.9317
-1.500 0.2590 0.01737 0.01202 -0.0866 0.7699 0.9571
-1.250 0.3585 0.01739 0.01176 -0.1005 0.7700 0.9817
-1.000 0.4472 0.01699 0.01115 -0.1131 0.7694 0.9986
-0.750 0.4748 0.01684 0.01088 -0.1134 0.7673 1.0000
-0.500 0.4914 0.01716 0.01116 -0.1122 0.7623 1.0000
-0.250 0.5093 0.01734 0.01129 -0.1110 0.7576 1.0000
0.000 0.5307 0.01725 0.01113 -0.1099 0.7548 1.0000
0.250 0.5534 0.01711 0.01091 -0.1090 0.7527 1.0000
0.500 0.5656 0.01770 0.01153 -0.1072 0.7455 1.0000
0.750 0.5864 0.01769 0.01147 -0.1062 0.7423 1.0000
1.000 0.6096 0.01754 0.01127 -0.1053 0.7401 1.0000
1.250 0.6232 0.01800 0.01175 -0.1034 0.7341 1.0000
1.500 0.6416 0.01814 0.01189 -0.1021 0.7298 1.0000
1.750 0.6654 0.01796 0.01168 -0.1013 0.7274 1.0000
2.000 0.6901 0.01779 0.01147 -0.1006 0.7256 1.0000
2.250 0.6966 0.01858 0.01232 -0.0977 0.7173 1.0000
2.500 0.7202 0.01845 0.01218 -0.0969 0.7147 1.0000
2.750 0.7464 0.01819 0.01193 -0.0963 0.7127 1.0000
3.000 0.7534 0.01890 0.01270 -0.0933 0.7050 1.0000
3.250 0.7771 0.01876 0.01258 -0.0925 0.7019 1.0000
3.500 0.8043 0.01848 0.01230 -0.0922 0.6998 1.0000
3.750 0.8310 0.01825 0.01209 -0.0918 0.6975 1.0000
4.000 0.8371 0.01896 0.01287 -0.0885 0.6890 1.0000
4.250 0.8653 0.01866 0.01265 -0.0883 0.6867 1.0000
4.500 0.8954 0.01834 0.01237 -0.0885 0.6850 1.0000
4.750 0.9000 0.01913 0.01326 -0.0850 0.6762 1.0000
5.000 0.9299 0.01876 0.01294 -0.0851 0.6736 1.0000
5.250 0.9627 0.01831 0.01256 -0.0856 0.6716 1.0000
5.500 0.9688 0.01903 0.01343 -0.0823 0.6629 1.0000
5.750 0.9996 0.01867 0.01316 -0.0826 0.6600 1.0000
6.000 1.0347 0.01816 0.01275 -0.0834 0.6578 1.0000
6.250 1.0447 0.01855 0.01328 -0.0805 0.6484 1.0000
6.500 1.0977 0.01541 0.01009 -0.0820 0.6299 1.0000
6.750 1.1083 0.01438 0.00907 -0.0775 0.5929 1.0000
7.000 1.1175 0.01415 0.00867 -0.0733 0.5478 1.0000
7.250 1.1030 0.01490 0.00890 -0.0653 0.4563 1.0000
7.500 1.0739 0.01636 0.00981 -0.0557 0.3766 1.0000
7.750 1.0407 0.01884 0.01165 -0.0477 0.2864 1.0000
8.000 1.0215 0.02136 0.01369 -0.0424 0.2030 1.0000
8.250 1.0027 0.02418 0.01594 -0.0378 0.1154 1.0000
8.500 0.9804 0.02753 0.01866 -0.0331 0.0369 1.0000
8.750 0.9772 0.02977 0.02093 -0.0301 0.0247 1.0000
9.000 0.9826 0.03139 0.02269 -0.0282 0.0220 1.0000
9.250 0.9843 0.03337 0.02479 -0.0260 0.0202 1.0000
9.500 0.9877 0.03521 0.02673 -0.0242 0.0198 1.0000
9.750 0.9909 0.03712 0.02873 -0.0223 0.0194 1.0000
10.000 0.9969 0.03883 0.03050 -0.0207 0.0191 1.0000
10.250 1.0016 0.04073 0.03245 -0.0186 0.0184 1.0000
10.500 1.0146 0.04206 0.03383 -0.0169 0.0185 1.0000
10.750 1.0327 0.04347 0.03531 -0.0149 0.0156 1.0000
11.000 1.0626 0.04454 0.03653 -0.0138 0.0159 1.0000
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Polar data table (+)
Polar graphs
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