AH 93-157 (ah93157-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 50,000 Max Cl/Cd: 14.44 at α=12.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93157-il-50000-n5.txt Download as CSV file: xf-ah93157-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3073 0.11380 0.10715 -0.0722 0.9698 0.0611
-11.000 -0.3038 0.10917 0.10252 -0.0754 0.9643 0.0610
-10.750 -0.2993 0.10418 0.09752 -0.0793 0.9599 0.0609
-10.500 -0.2983 0.09836 0.09170 -0.0845 0.9559 0.0610
-10.250 -0.3006 0.09333 0.08668 -0.0880 0.9497 0.0608
-10.000 -0.3030 0.08711 0.08043 -0.0935 0.9448 0.0606
-9.750 -0.3105 0.08148 0.07475 -0.0981 0.9394 0.0602
-9.500 -0.3252 0.07726 0.07047 -0.0998 0.9320 0.0599
-9.250 -0.3387 0.07281 0.06589 -0.1017 0.9264 0.0596
-9.000 -0.3623 0.07072 0.06373 -0.0983 0.9172 0.0593
-8.750 -0.3730 0.06699 0.05978 -0.0979 0.9115 0.0591
-8.500 -0.3929 0.06488 0.05752 -0.0937 0.9033 0.0591
-8.250 -0.4014 0.06179 0.05414 -0.0917 0.8977 0.0591
-8.000 -0.4110 0.05917 0.05121 -0.0884 0.8917 0.0594
-7.750 -0.4202 0.05694 0.04868 -0.0845 0.8850 0.0598
-7.500 -0.4187 0.05383 0.04497 -0.0825 0.8806 0.0611
-7.250 -0.4196 0.05228 0.04329 -0.0790 0.8748 0.0625
-7.000 -0.4131 0.05090 0.04179 -0.0766 0.8695 0.0640
-6.750 -0.3977 0.04890 0.03947 -0.0757 0.8658 0.0660
-6.500 -0.3801 0.04671 0.03685 -0.0748 0.8625 0.0677
-6.250 -0.3826 0.04570 0.03559 -0.0702 0.8558 0.0693
-6.000 -0.3650 0.04399 0.03331 -0.0688 0.8517 0.0728
-5.750 -0.3386 0.04244 0.03164 -0.0692 0.8489 0.0766
-5.500 -0.3251 0.04151 0.03053 -0.0671 0.8442 0.0793
-5.250 -0.3115 0.04071 0.02946 -0.0649 0.8390 0.0838
-5.000 -0.2850 0.03963 0.02822 -0.0649 0.8356 0.0895
-4.750 -0.2520 0.03869 0.02711 -0.0659 0.8330 0.0973
-4.500 -0.2351 0.03818 0.02653 -0.0642 0.8284 0.1044
-4.250 -0.2183 0.03782 0.02605 -0.0625 0.8232 0.1130
-4.000 -0.1892 0.03724 0.02544 -0.0628 0.8197 0.1261
-3.750 -0.1567 0.03661 0.02475 -0.0637 0.8170 0.1454
-3.500 -0.1482 0.03644 0.02461 -0.0608 0.8114 0.1617
-3.250 -0.1351 0.03607 0.02442 -0.0587 0.8061 0.1877
-3.000 -0.1134 0.03533 0.02402 -0.0581 0.8025 0.2442
-2.750 -0.0960 0.03412 0.02366 -0.0567 0.7997 0.3801
-2.500 -0.0505 0.03501 0.02622 -0.0549 0.7967 0.8036
-2.250 -0.0646 0.03557 0.02664 -0.0474 0.7893 0.8541
-2.000 0.1979 0.03641 0.02635 -0.0866 0.8002 0.9704
-1.750 0.3087 0.03569 0.02520 -0.1032 0.8002 0.9973
-1.500 0.3039 0.03648 0.02593 -0.0990 0.7913 1.0000
-1.250 0.3224 0.03665 0.02594 -0.0981 0.7865 1.0000
-1.000 0.3281 0.03715 0.02632 -0.0951 0.7803 1.0000
-0.750 0.3282 0.03771 0.02680 -0.0912 0.7727 1.0000
-0.500 0.3536 0.03781 0.02676 -0.0912 0.7690 1.0000
-0.250 0.3350 0.03873 0.02764 -0.0843 0.7592 1.0000
0.000 0.3554 0.03893 0.02773 -0.0835 0.7544 1.0000
0.500 0.3604 0.04002 0.02868 -0.0763 0.7401 1.0000
0.750 0.3884 0.04011 0.02866 -0.0766 0.7366 1.0000
1.000 0.3702 0.04104 0.02957 -0.0700 0.7261 1.0000
1.250 0.3945 0.04119 0.02963 -0.0696 0.7219 1.0000
1.500 0.3848 0.04198 0.03039 -0.0643 0.7124 1.0000
1.750 0.4042 0.04221 0.03055 -0.0632 0.7073 1.0000
2.000 0.4036 0.04285 0.03116 -0.0593 0.6992 1.0000
2.250 0.4164 0.04320 0.03145 -0.0572 0.6927 1.0000
2.500 0.4455 0.04322 0.03142 -0.0573 0.6893 1.0000
2.750 0.4306 0.04416 0.03235 -0.0516 0.6783 1.0000
3.000 0.4583 0.04417 0.03232 -0.0515 0.6745 1.0000
3.250 0.4463 0.04510 0.03324 -0.0463 0.6637 1.0000
3.500 0.4728 0.04511 0.03321 -0.0459 0.6596 1.0000
3.750 0.4636 0.04603 0.03412 -0.0412 0.6490 1.0000
4.000 0.4890 0.04604 0.03412 -0.0407 0.6447 1.0000
4.250 0.4824 0.04696 0.03504 -0.0365 0.6341 1.0000
4.500 0.5072 0.04699 0.03506 -0.0358 0.6297 1.0000
4.750 0.5035 0.04792 0.03600 -0.0321 0.6191 1.0000
5.000 0.5290 0.04794 0.03603 -0.0316 0.6146 1.0000
5.250 0.5278 0.04898 0.03707 -0.0285 0.6040 1.0000
5.500 0.5545 0.04897 0.03709 -0.0282 0.5994 1.0000
5.750 0.5553 0.05012 0.03825 -0.0256 0.5886 1.0000
6.000 0.5837 0.05006 0.03824 -0.0254 0.5841 1.0000
6.250 0.5852 0.05136 0.03958 -0.0232 0.5731 1.0000
6.500 0.6152 0.05120 0.03947 -0.0231 0.5687 1.0000
6.750 0.6172 0.05262 0.04092 -0.0212 0.5573 1.0000
7.000 0.6481 0.05239 0.04078 -0.0212 0.5531 1.0000
7.250 0.6502 0.05393 0.04238 -0.0194 0.5414 1.0000
7.500 0.6823 0.05359 0.04212 -0.0194 0.5375 1.0000
7.750 0.6843 0.05525 0.04383 -0.0178 0.5254 1.0000
8.250 0.7187 0.05659 0.04537 -0.0163 0.5092 1.0000
8.750 0.7535 0.05793 0.04690 -0.0149 0.4930 1.0000
9.000 0.7584 0.05968 0.04876 -0.0138 0.4815 1.0000
9.250 0.7889 0.05920 0.04842 -0.0135 0.4769 1.0000
9.750 0.8250 0.06031 0.04978 -0.0121 0.4607 1.0000
10.000 0.8256 0.06263 0.05222 -0.0111 0.4480 1.0000
10.500 0.8609 0.06378 0.05365 -0.0097 0.4313 1.0000
11.000 0.8981 0.06465 0.05483 -0.0083 0.4148 1.0000
11.250 0.8971 0.06732 0.05762 -0.0075 0.4018 1.0000
11.750 0.9361 0.06779 0.05842 -0.0060 0.3847 1.0000
12.000 0.9362 0.07038 0.06116 -0.0054 0.3720 1.0000
12.250 0.9778 0.06772 0.05872 -0.0043 0.3665 1.0000
12.500 0.9815 0.06974 0.06089 -0.0035 0.3538 1.0000
12.750 0.9822 0.07220 0.06348 -0.0030 0.3408 1.0000
13.000 0.9916 0.07347 0.06491 -0.0022 0.3285 1.0000
13.250 1.0156 0.07255 0.06418 -0.0011 0.3165 1.0000
13.500 1.0317 0.07251 0.06427 0.0000 0.3015 1.0000
13.750 1.0399 0.07352 0.06538 0.0009 0.2846 1.0000
14.000 1.0464 0.07481 0.06676 0.0016 0.2666 1.0000
14.250 1.0565 0.07552 0.06750 0.0025 0.2469 1.0000
14.500 1.0561 0.07807 0.07009 0.0027 0.2282 1.0000
14.750 1.0526 0.08125 0.07332 0.0026 0.2090 1.0000
15.000 1.0525 0.08386 0.07588 0.0026 0.1885 1.0000
15.250 1.0484 0.08729 0.07927 0.0023 0.1690 1.0000
15.500 1.0432 0.09102 0.08295 0.0017 0.1502 1.0000
15.750 1.0381 0.09482 0.08662 0.0011 0.1334 1.0000
16.000 1.0329 0.09876 0.09046 0.0003 0.1191 1.0000
16.250 1.0282 0.10278 0.09442 -0.0007 0.1070 1.0000
16.500 1.0248 0.10672 0.09833 -0.0017 0.0967 1.0000
16.750 1.0227 0.11048 0.10206 -0.0027 0.0883 1.0000
17.000 1.0219 0.11408 0.10563 -0.0038 0.0811 1.0000
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Polar data table (+)
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