AH 80-129 (ah80129-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.31 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80129-il-1000000.txt Download as CSV file: xf-ah80129-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2272 0.09591 0.09340 -0.0690 0.7818 0.0071
-10.000 -0.2213 0.09163 0.08910 -0.0721 0.7800 0.0076
-9.750 -0.2198 0.08668 0.08418 -0.0752 0.7785 0.0068
-9.500 -0.2123 0.08328 0.08079 -0.0778 0.7766 0.0090
-9.250 -0.2061 0.08037 0.07788 -0.0799 0.7748 0.0082
-9.000 -0.1977 0.07620 0.07373 -0.0836 0.7726 0.0095
-6.500 -0.2246 0.02806 0.02436 -0.0913 0.7493 0.0110
-6.250 -0.2151 0.02533 0.02136 -0.0886 0.7470 0.0110
-6.000 -0.1998 0.02391 0.01979 -0.0870 0.7446 0.0115
-5.750 -0.1826 0.02267 0.01842 -0.0855 0.7425 0.0122
-5.500 -0.1732 0.01818 0.01327 -0.0812 0.7404 0.0107
-4.750 -0.1085 0.01413 0.00861 -0.0775 0.7338 0.0106
-4.500 -0.0829 0.01379 0.00820 -0.0771 0.7313 0.0102
-4.250 -0.0605 0.01219 0.00644 -0.0759 0.7292 0.0096
-4.000 -0.0379 0.01117 0.00529 -0.0748 0.7270 0.0095
-3.750 -0.0153 0.01049 0.00448 -0.0738 0.7248 0.0094
-3.500 0.0082 0.01001 0.00393 -0.0729 0.7226 0.0099
-3.250 0.0315 0.00955 0.00340 -0.0720 0.7200 0.0097
-3.000 0.0540 0.00900 0.00273 -0.0708 0.7173 0.0120
-2.750 0.0793 0.00878 0.00247 -0.0704 0.7149 0.0136
-2.500 0.1053 0.00863 0.00225 -0.0700 0.7125 0.0142
-2.250 0.1297 0.00835 0.00205 -0.0694 0.7101 0.0378
-2.000 0.1540 0.00809 0.00192 -0.0688 0.7074 0.0764
-1.750 0.1763 0.00768 0.00180 -0.0680 0.7047 0.1610
-1.500 0.1980 0.00728 0.00169 -0.0670 0.7019 0.2612
-1.250 0.2173 0.00678 0.00160 -0.0656 0.6993 0.4040
-1.000 0.2285 0.00602 0.00154 -0.0624 0.6964 0.6222
-0.750 0.2372 0.00545 0.00157 -0.0581 0.6933 0.8051
-0.500 0.2618 0.00532 0.00159 -0.0574 0.6904 0.8629
-0.250 0.2899 0.00530 0.00157 -0.0575 0.6875 0.8859
0.000 0.3214 0.00531 0.00157 -0.0583 0.6845 0.9092
0.250 0.3528 0.00530 0.00159 -0.0592 0.6817 0.9268
0.500 0.3932 0.00533 0.00163 -0.0621 0.6784 0.9437
0.750 0.4282 0.00538 0.00165 -0.0638 0.6752 0.9546
1.000 0.4724 0.00546 0.00169 -0.0676 0.6723 0.9593
1.250 0.5117 0.00554 0.00175 -0.0703 0.6693 0.9639
1.500 0.5440 0.00561 0.00182 -0.0714 0.6655 0.9698
1.750 0.5853 0.00570 0.00190 -0.0745 0.6618 0.9718
2.000 0.6215 0.00579 0.00193 -0.0766 0.6578 0.9735
2.250 0.6561 0.00583 0.00199 -0.0784 0.6535 0.9755
2.500 0.6885 0.00588 0.00204 -0.0796 0.6495 0.9780
2.750 0.7168 0.00594 0.00209 -0.0800 0.6455 0.9816
3.000 0.7517 0.00599 0.00215 -0.0819 0.6413 0.9825
3.250 0.7862 0.00603 0.00221 -0.0837 0.6373 0.9837
3.500 0.8196 0.00608 0.00226 -0.0852 0.6322 0.9852
3.750 0.8521 0.00614 0.00233 -0.0866 0.6277 0.9871
4.000 0.8833 0.00620 0.00244 -0.0877 0.6227 0.9895
4.250 0.9156 0.00628 0.00250 -0.0890 0.6168 0.9911
4.500 0.9496 0.00632 0.00260 -0.0908 0.6110 0.9923
4.750 0.9809 0.00644 0.00265 -0.0919 0.5882 0.9943
5.000 1.0108 0.00666 0.00279 -0.0929 0.5585 0.9965
5.250 1.0406 0.00699 0.00299 -0.0939 0.5215 0.9988
5.500 1.0509 0.00795 0.00348 -0.0913 0.4294 1.0000
5.750 1.0544 0.00864 0.00391 -0.0871 0.3749 1.0000
6.000 1.0357 0.01006 0.00477 -0.0788 0.2716 1.0000
6.250 1.0407 0.01064 0.00522 -0.0748 0.2390 1.0000
6.500 1.0372 0.01154 0.00588 -0.0694 0.1906 1.0000
6.750 1.0170 0.01287 0.00686 -0.0613 0.1216 1.0000
7.000 1.0093 0.01445 0.00811 -0.0566 0.0591 1.0000
7.250 1.0047 0.01623 0.00963 -0.0527 0.0079 1.0000
7.500 1.0156 0.01723 0.01072 -0.0508 0.0054 1.0000
7.750 1.0289 0.01810 0.01166 -0.0494 0.0052 1.0000
8.000 1.0445 0.01884 0.01245 -0.0483 0.0050 1.0000
8.250 1.0596 0.01961 0.01325 -0.0472 0.0045 1.0000
8.500 1.0714 0.02063 0.01434 -0.0457 0.0044 1.0000
8.750 1.0767 0.02213 0.01597 -0.0434 0.0047 1.0000
9.000 1.0854 0.02341 0.01732 -0.0417 0.0046 1.0000
9.250 1.0967 0.02453 0.01849 -0.0404 0.0042 1.0000
9.500 1.1062 0.02577 0.01979 -0.0389 0.0040 1.0000
9.750 1.1152 0.02708 0.02116 -0.0375 0.0039 1.0000
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Polar data table (+)
Polar graphs
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