AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 500,000 Max Cl/Cd: 82.85 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-7-il-500000-n5.txt Download as CSV file: xf-ah21-7-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5242 0.08543 0.08313 -0.0367 0.9983 0.0100
-9.500 -0.5312 0.07725 0.07497 -0.0437 0.9961 0.0101
-9.250 -0.5468 0.06613 0.06389 -0.0554 0.9922 0.0102
-9.000 -0.6240 0.03418 0.03080 -0.0769 0.9783 0.0103
-8.750 -0.6174 0.02849 0.02445 -0.0775 0.9746 0.0108
-8.500 -0.5976 0.02539 0.02088 -0.0781 0.9728 0.0111
-8.250 -0.5729 0.02355 0.01869 -0.0788 0.9717 0.0114
-8.000 -0.5493 0.02165 0.01647 -0.0792 0.9704 0.0116
-7.750 -0.5363 0.02000 0.01459 -0.0771 0.9658 0.0120
-7.500 -0.5116 0.01914 0.01364 -0.0771 0.9637 0.0124
-7.250 -0.4845 0.01842 0.01283 -0.0774 0.9621 0.0129
-7.000 -0.4566 0.01763 0.01192 -0.0779 0.9609 0.0134
-6.750 -0.4282 0.01672 0.01087 -0.0785 0.9598 0.0138
-6.500 -0.3989 0.01590 0.00991 -0.0791 0.9589 0.0142
-6.250 -0.3689 0.01514 0.00903 -0.0799 0.9581 0.0147
-6.000 -0.3384 0.01447 0.00826 -0.0807 0.9575 0.0150
-5.750 -0.3237 0.01402 0.00775 -0.0780 0.9519 0.0153
-5.500 -0.2964 0.01350 0.00714 -0.0781 0.9499 0.0156
-5.250 -0.2681 0.01282 0.00641 -0.0784 0.9483 0.0163
-5.000 -0.2385 0.01224 0.00579 -0.0791 0.9471 0.0171
-4.750 -0.2077 0.01179 0.00531 -0.0799 0.9460 0.0178
-4.500 -0.1762 0.01139 0.00486 -0.0808 0.9452 0.0186
-4.250 -0.1439 0.01103 0.00447 -0.0819 0.9444 0.0194
-4.000 -0.1217 0.01079 0.00419 -0.0807 0.9405 0.0201
-3.750 -0.0959 0.01054 0.00391 -0.0802 0.9372 0.0209
-3.500 -0.0659 0.01024 0.00358 -0.0807 0.9353 0.0226
-3.250 -0.0344 0.00997 0.00332 -0.0816 0.9337 0.0265
-3.000 -0.0020 0.00965 0.00307 -0.0827 0.9324 0.0407
-2.750 0.0307 0.00931 0.00284 -0.0838 0.9311 0.0706
-2.500 0.0638 0.00897 0.00265 -0.0851 0.9299 0.1090
-2.250 0.0822 0.00871 0.00255 -0.0832 0.9235 0.1538
-2.000 0.1113 0.00830 0.00239 -0.0837 0.9205 0.2292
-1.750 0.1424 0.00777 0.00225 -0.0847 0.9181 0.3396
-1.500 0.1743 0.00722 0.00212 -0.0858 0.9160 0.4663
-1.250 0.1946 0.00694 0.00209 -0.0842 0.9088 0.5402
-1.000 0.2240 0.00657 0.00202 -0.0846 0.9045 0.6327
-0.750 0.2528 0.00634 0.00196 -0.0846 0.8992 0.6893
-0.500 0.2790 0.00616 0.00193 -0.0841 0.8916 0.7372
-0.250 0.3079 0.00601 0.00188 -0.0841 0.8840 0.7760
0.000 0.3377 0.00589 0.00182 -0.0842 0.8747 0.8084
0.250 0.3646 0.00581 0.00180 -0.0837 0.8626 0.8350
0.500 0.3932 0.00575 0.00175 -0.0836 0.8480 0.8574
0.750 0.4215 0.00573 0.00171 -0.0834 0.8297 0.8764
1.000 0.4482 0.00575 0.00169 -0.0828 0.8058 0.8935
1.250 0.4735 0.00584 0.00168 -0.0819 0.7748 0.9091
1.500 0.4963 0.00599 0.00169 -0.0805 0.7358 0.9240
1.750 0.5164 0.00624 0.00174 -0.0786 0.6864 0.9388
2.000 0.5360 0.00659 0.00182 -0.0766 0.6270 0.9539
2.250 0.5588 0.00702 0.00197 -0.0756 0.5593 0.9679
2.500 0.5852 0.00753 0.00215 -0.0755 0.4838 0.9804
2.750 0.6143 0.00807 0.00235 -0.0762 0.4098 0.9923
3.000 0.6374 0.00858 0.00257 -0.0755 0.3437 1.0000
3.250 0.6561 0.00901 0.00276 -0.0738 0.2913 1.0000
3.500 0.6763 0.00943 0.00296 -0.0725 0.2445 1.0000
3.750 0.6975 0.00984 0.00317 -0.0713 0.2040 1.0000
4.000 0.7194 0.01022 0.00341 -0.0703 0.1699 1.0000
4.250 0.7418 0.01058 0.00364 -0.0693 0.1419 1.0000
4.500 0.7644 0.01095 0.00388 -0.0684 0.1185 1.0000
4.750 0.7876 0.01127 0.00413 -0.0676 0.1012 1.0000
5.000 0.8109 0.01159 0.00440 -0.0668 0.0875 1.0000
5.250 0.8341 0.01192 0.00468 -0.0660 0.0754 1.0000
5.500 0.8572 0.01226 0.00497 -0.0652 0.0650 1.0000
5.750 0.8805 0.01258 0.00527 -0.0645 0.0574 1.0000
6.000 0.9037 0.01291 0.00559 -0.0637 0.0510 1.0000
6.250 0.9265 0.01327 0.00594 -0.0628 0.0451 1.0000
6.500 0.9495 0.01361 0.00630 -0.0620 0.0413 1.0000
6.750 0.9723 0.01396 0.00666 -0.0612 0.0380 1.0000
7.000 0.9942 0.01440 0.00708 -0.0602 0.0345 1.0000
7.250 1.0166 0.01477 0.00752 -0.0592 0.0323 1.0000
7.500 1.0388 0.01515 0.00793 -0.0583 0.0301 1.0000
7.750 1.0604 0.01558 0.00838 -0.0573 0.0280 1.0000
8.000 1.0808 0.01612 0.00894 -0.0561 0.0261 1.0000
8.250 1.1014 0.01662 0.00950 -0.0549 0.0249 1.0000
8.500 1.1219 0.01707 0.01004 -0.0537 0.0239 1.0000
8.750 1.1417 0.01754 0.01057 -0.0524 0.0227 1.0000
9.000 1.1611 0.01802 0.01109 -0.0510 0.0215 1.0000
9.250 1.1794 0.01858 0.01169 -0.0495 0.0204 1.0000
9.500 1.1946 0.01940 0.01255 -0.0475 0.0191 1.0000
9.750 1.2139 0.01984 0.01307 -0.0461 0.0184 1.0000
10.000 1.2320 0.02036 0.01369 -0.0447 0.0175 1.0000
10.250 1.2500 0.02088 0.01427 -0.0432 0.0165 1.0000
10.500 1.2672 0.02145 0.01490 -0.0417 0.0157 1.0000
10.750 1.2827 0.02216 0.01566 -0.0399 0.0149 1.0000
11.000 1.2955 0.02306 0.01664 -0.0377 0.0142 1.0000
11.250 1.3109 0.02374 0.01743 -0.0360 0.0137 1.0000
11.500 1.3263 0.02441 0.01822 -0.0344 0.0130 1.0000
11.750 1.3403 0.02518 0.01908 -0.0326 0.0123 1.0000
12.000 1.3547 0.02588 0.01985 -0.0309 0.0116 1.0000
12.250 1.3670 0.02676 0.02079 -0.0290 0.0110 1.0000
12.500 1.3758 0.02790 0.02202 -0.0268 0.0105 1.0000
12.750 1.3866 0.02890 0.02316 -0.0248 0.0100 1.0000
13.000 1.3959 0.03000 0.02440 -0.0228 0.0096 1.0000
13.250 1.4041 0.03120 0.02572 -0.0208 0.0091 1.0000
13.500 1.4118 0.03244 0.02708 -0.0189 0.0087 1.0000
13.750 1.4190 0.03375 0.02850 -0.0171 0.0083 1.0000
14.000 1.4234 0.03532 0.03017 -0.0152 0.0079 1.0000
14.250 1.4236 0.03729 0.03227 -0.0132 0.0076 1.0000
14.500 1.4239 0.03935 0.03448 -0.0114 0.0074 1.0000
14.750 1.4238 0.04153 0.03682 -0.0099 0.0072 1.0000
15.000 1.4214 0.04403 0.03948 -0.0087 0.0070 1.0000
15.250 1.4180 0.04678 0.04240 -0.0078 0.0068 1.0000
15.500 1.4119 0.05002 0.04579 -0.0074 0.0066 1.0000
15.750 1.4037 0.05376 0.04969 -0.0075 0.0065 1.0000
16.000 1.3950 0.05786 0.05396 -0.0082 0.0063 1.0000
16.250 1.3827 0.06287 0.05914 -0.0098 0.0062 1.0000
16.500 1.3677 0.06880 0.06525 -0.0124 0.0061 1.0000
16.750 1.3491 0.07597 0.07260 -0.0161 0.0061 1.0000
17.000 1.3215 0.08564 0.08248 -0.0218 0.0062 1.0000
17.250 1.2875 0.09749 0.09456 -0.0290 0.0063 1.0000
17.500 1.2425 0.11237 0.10967 -0.0380 0.0066 1.0000
17.750 1.1956 0.12805 0.12554 -0.0472 0.0068 1.0000
18.000 1.1499 0.14397 0.14161 -0.0567 0.0071 1.0000
18.250 1.1086 0.15961 0.15734 -0.0660 0.0074 1.0000
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