AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.62 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-9-il-1000000-n5.txt Download as CSV file: xf-ah21-9-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5339 0.09664 0.09497 -0.0214 1.0000 0.0032
-9.000 -0.7081 0.02019 0.01664 -0.0649 0.9859 0.0036
-8.750 -0.6844 0.01791 0.01396 -0.0654 0.9848 0.0038
-8.500 -0.6579 0.01650 0.01230 -0.0661 0.9839 0.0039
-8.250 -0.6310 0.01504 0.01058 -0.0667 0.9832 0.0041
-8.000 -0.6025 0.01416 0.00957 -0.0674 0.9827 0.0046
-7.750 -0.5790 0.01393 0.00933 -0.0667 0.9805 0.0050
-7.500 -0.5524 0.01389 0.00929 -0.0666 0.9787 0.0054
-7.250 -0.5251 0.01355 0.00890 -0.0668 0.9772 0.0059
-7.000 -0.4970 0.01313 0.00839 -0.0671 0.9759 0.0064
-6.750 -0.4686 0.01257 0.00773 -0.0675 0.9747 0.0068
-6.500 -0.4394 0.01217 0.00726 -0.0681 0.9738 0.0070
-6.250 -0.4107 0.01140 0.00640 -0.0686 0.9728 0.0078
-6.000 -0.3803 0.01120 0.00620 -0.0694 0.9721 0.0083
-5.750 -0.3495 0.01095 0.00590 -0.0703 0.9715 0.0089
-5.500 -0.3184 0.01069 0.00562 -0.0712 0.9709 0.0098
-5.250 -0.2872 0.01036 0.00523 -0.0721 0.9703 0.0106
-5.000 -0.2563 0.00996 0.00478 -0.0729 0.9697 0.0112
-4.750 -0.2339 0.00966 0.00444 -0.0718 0.9662 0.0115
-4.500 -0.2063 0.00947 0.00423 -0.0718 0.9639 0.0118
-4.250 -0.1785 0.00882 0.00348 -0.0720 0.9620 0.0130
-4.000 -0.1489 0.00841 0.00303 -0.0725 0.9604 0.0138
-3.750 -0.1185 0.00811 0.00270 -0.0731 0.9589 0.0144
-3.500 -0.0879 0.00785 0.00241 -0.0738 0.9576 0.0149
-3.250 -0.0566 0.00762 0.00215 -0.0746 0.9562 0.0153
-3.000 -0.0323 0.00744 0.00194 -0.0738 0.9520 0.0157
-2.750 -0.0042 0.00726 0.00175 -0.0738 0.9486 0.0165
-2.500 0.0254 0.00709 0.00155 -0.0742 0.9457 0.0169
-2.250 0.0568 0.00692 0.00137 -0.0750 0.9432 0.0176
-2.000 0.0828 0.00681 0.00123 -0.0745 0.9377 0.0187
-1.750 0.1114 0.00662 0.00110 -0.0746 0.9325 0.0335
-1.500 0.1401 0.00635 0.00098 -0.0749 0.9267 0.0801
-1.250 0.1676 0.00606 0.00088 -0.0749 0.9186 0.1441
-1.000 0.1946 0.00568 0.00078 -0.0749 0.9089 0.2436
-0.750 0.2217 0.00530 0.00071 -0.0749 0.8968 0.3515
-0.500 0.2479 0.00490 0.00065 -0.0748 0.8808 0.4813
-0.250 0.2723 0.00442 0.00064 -0.0742 0.8599 0.6525
0.000 0.2961 0.00423 0.00065 -0.0732 0.8314 0.7482
0.250 0.3193 0.00428 0.00066 -0.0720 0.7910 0.7887
0.500 0.3405 0.00446 0.00071 -0.0704 0.7357 0.8215
0.750 0.3601 0.00475 0.00079 -0.0684 0.6646 0.8496
1.000 0.3805 0.00506 0.00090 -0.0668 0.5952 0.8743
1.250 0.3999 0.00547 0.00103 -0.0650 0.5072 0.8963
1.500 0.4191 0.00597 0.00118 -0.0632 0.4070 0.9164
1.750 0.4409 0.00628 0.00130 -0.0619 0.3482 0.9351
2.000 0.4642 0.00655 0.00142 -0.0610 0.2980 0.9524
2.250 0.4897 0.00693 0.00156 -0.0606 0.2354 0.9683
2.500 0.5201 0.00725 0.00170 -0.0614 0.1879 0.9810
2.750 0.5521 0.00764 0.00187 -0.0626 0.1367 0.9922
3.000 0.5799 0.00799 0.00206 -0.0628 0.0975 1.0000
3.250 0.6044 0.00824 0.00221 -0.0622 0.0780 1.0000
3.500 0.6294 0.00847 0.00238 -0.0617 0.0631 1.0000
3.750 0.6544 0.00871 0.00256 -0.0612 0.0502 1.0000
4.000 0.6795 0.00896 0.00275 -0.0607 0.0402 1.0000
4.250 0.7049 0.00917 0.00296 -0.0603 0.0343 1.0000
4.500 0.7301 0.00942 0.00318 -0.0598 0.0274 1.0000
4.750 0.7554 0.00967 0.00341 -0.0594 0.0234 1.0000
5.000 0.7804 0.00995 0.00368 -0.0589 0.0193 1.0000
5.250 0.8057 0.01020 0.00395 -0.0584 0.0180 1.0000
5.500 0.8309 0.01046 0.00426 -0.0580 0.0170 1.0000
5.750 0.8559 0.01075 0.00457 -0.0575 0.0160 1.0000
6.000 0.8807 0.01107 0.00490 -0.0570 0.0150 1.0000
6.250 0.9049 0.01146 0.00530 -0.0563 0.0133 1.0000
6.500 0.9289 0.01188 0.00578 -0.0557 0.0122 1.0000
6.750 0.9536 0.01219 0.00612 -0.0552 0.0118 1.0000
7.000 0.9782 0.01250 0.00648 -0.0547 0.0113 1.0000
7.250 1.0028 0.01281 0.00684 -0.0542 0.0105 1.0000
7.500 1.0271 0.01314 0.00720 -0.0537 0.0096 1.0000
7.750 1.0510 0.01352 0.00759 -0.0531 0.0088 1.0000
8.000 1.0739 0.01406 0.00818 -0.0523 0.0078 1.0000
8.250 1.0975 0.01445 0.00863 -0.0517 0.0074 1.0000
8.500 1.1213 0.01482 0.00905 -0.0511 0.0069 1.0000
8.750 1.1448 0.01521 0.00948 -0.0505 0.0061 1.0000
9.000 1.1678 0.01566 0.00996 -0.0499 0.0052 1.0000
9.250 1.1898 0.01625 0.01060 -0.0490 0.0044 1.0000
9.500 1.2118 0.01681 0.01123 -0.0482 0.0040 1.0000
9.750 1.2335 0.01739 0.01188 -0.0473 0.0036 1.0000
10.000 1.2545 0.01805 0.01262 -0.0464 0.0032 1.0000
10.250 1.2749 0.01878 0.01342 -0.0453 0.0029 1.0000
10.500 1.2939 0.01970 0.01446 -0.0441 0.0026 1.0000
10.750 1.3110 0.02083 0.01575 -0.0425 0.0023 1.0000
11.000 1.3295 0.02167 0.01673 -0.0413 0.0023 1.0000
11.250 1.3467 0.02262 0.01782 -0.0399 0.0022 1.0000
11.500 1.3634 0.02358 0.01891 -0.0384 0.0022 1.0000
11.750 1.3784 0.02466 0.02015 -0.0367 0.0021 1.0000
12.000 1.3916 0.02588 0.02152 -0.0348 0.0021 1.0000
12.250 1.4035 0.02711 0.02292 -0.0327 0.0020 1.0000
12.500 1.4129 0.02839 0.02435 -0.0303 0.0019 1.0000
12.750 1.4181 0.02973 0.02586 -0.0273 0.0019 1.0000
13.000 1.4199 0.03126 0.02756 -0.0239 0.0018 1.0000
13.250 1.4197 0.03294 0.02941 -0.0205 0.0018 1.0000
13.500 1.4187 0.03468 0.03131 -0.0174 0.0018 1.0000
13.750 1.4151 0.03669 0.03349 -0.0144 0.0017 1.0000
14.000 1.4079 0.03909 0.03608 -0.0116 0.0017 1.0000
14.250 1.3981 0.04186 0.03903 -0.0092 0.0017 1.0000
14.500 1.3879 0.04490 0.04223 -0.0076 0.0016 1.0000
14.750 1.3746 0.04858 0.04608 -0.0068 0.0016 1.0000
15.000 1.3448 0.05491 0.05264 -0.0078 0.0017 1.0000
15.250 1.3206 0.06185 0.05976 -0.0111 0.0016 1.0000
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Polar data table (+)
Polar graphs
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