AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 500,000 Max Cl/Cd: 99.21 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150f-il-500000-n5.txt Download as CSV file: xf-ah82150f-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 F
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1444 0.08655 0.08334 -0.1045 0.7959 0.0082
-12.000 -0.4269 0.04449 0.04097 -0.1365 0.7982 0.0067
-11.750 -0.4724 0.03847 0.03468 -0.1344 0.7967 0.0066
-11.500 -0.5035 0.03430 0.03019 -0.1304 0.7954 0.0066
-11.250 -0.5149 0.03186 0.02751 -0.1270 0.7941 0.0066
-11.000 -0.5251 0.02947 0.02484 -0.1231 0.7928 0.0068
-10.750 -0.5266 0.02780 0.02293 -0.1197 0.7917 0.0069
-10.500 -0.5219 0.02670 0.02161 -0.1169 0.7909 0.0071
-10.250 -0.5154 0.02531 0.01997 -0.1143 0.7900 0.0073
-10.000 -0.5074 0.02376 0.01818 -0.1119 0.7893 0.0075
-9.750 -0.4981 0.02218 0.01640 -0.1097 0.7885 0.0078
-9.500 -0.4827 0.02122 0.01530 -0.1083 0.7877 0.0080
-9.250 -0.4647 0.02047 0.01443 -0.1072 0.7870 0.0083
-9.000 -0.4458 0.01970 0.01354 -0.1062 0.7862 0.0086
-8.750 -0.4259 0.01899 0.01272 -0.1053 0.7854 0.0089
-8.500 -0.4053 0.01833 0.01195 -0.1045 0.7847 0.0093
-8.250 -0.3841 0.01769 0.01118 -0.1038 0.7840 0.0097
-8.000 -0.3626 0.01707 0.01045 -0.1031 0.7832 0.0102
-7.750 -0.3407 0.01650 0.00977 -0.1024 0.7824 0.0106
-7.500 -0.3183 0.01600 0.00917 -0.1018 0.7815 0.0110
-7.250 -0.2971 0.01537 0.00849 -0.1011 0.7807 0.0120
-7.000 -0.2736 0.01503 0.00811 -0.1007 0.7801 0.0131
-6.750 -0.2498 0.01470 0.00774 -0.1003 0.7794 0.0142
-6.500 -0.2261 0.01437 0.00734 -0.0999 0.7788 0.0154
-6.250 -0.2029 0.01397 0.00687 -0.0993 0.7782 0.0170
-6.000 -0.1789 0.01368 0.00656 -0.0990 0.7776 0.0190
-5.750 -0.1542 0.01345 0.00629 -0.0987 0.7771 0.0211
-5.500 -0.1291 0.01326 0.00605 -0.0985 0.7765 0.0228
-5.250 -0.1050 0.01299 0.00576 -0.0982 0.7759 0.0259
-5.000 -0.0803 0.01282 0.00560 -0.0979 0.7752 0.0293
-4.750 -0.0553 0.01270 0.00545 -0.0977 0.7744 0.0320
-4.500 -0.0314 0.01245 0.00520 -0.0973 0.7735 0.0356
-4.250 -0.0068 0.01228 0.00504 -0.0970 0.7727 0.0393
-4.000 0.0184 0.01216 0.00490 -0.0969 0.7719 0.0431
-3.750 0.0432 0.01200 0.00473 -0.0966 0.7711 0.0480
-3.500 0.0683 0.01186 0.00460 -0.0964 0.7703 0.0542
-3.250 0.0934 0.01171 0.00447 -0.0962 0.7694 0.0638
-3.000 0.1182 0.01153 0.00436 -0.0960 0.7684 0.0820
-2.750 0.1423 0.01129 0.00424 -0.0957 0.7676 0.1186
-2.500 0.1650 0.01094 0.00414 -0.0952 0.7667 0.1896
-2.250 0.1864 0.01049 0.00404 -0.0945 0.7658 0.2923
-2.000 0.2074 0.01001 0.00393 -0.0938 0.7649 0.4031
-1.750 0.2282 0.00951 0.00381 -0.0929 0.7640 0.5169
-1.500 0.2461 0.00882 0.00369 -0.0914 0.7629 0.6735
-1.250 0.2669 0.00899 0.00426 -0.0894 0.7617 0.8014
-1.000 0.2910 0.00928 0.00456 -0.0885 0.7597 0.8296
-0.750 0.3153 0.00956 0.00484 -0.0877 0.7578 0.8429
-0.500 0.3416 0.00964 0.00490 -0.0875 0.7559 0.8485
-0.250 0.3682 0.00972 0.00497 -0.0873 0.7541 0.8521
0.000 0.3954 0.00979 0.00500 -0.0872 0.7522 0.8585
0.250 0.4213 0.00990 0.00510 -0.0866 0.7504 0.8654
0.500 0.4488 0.00997 0.00513 -0.0864 0.7487 0.8719
0.750 0.4742 0.00997 0.00514 -0.0863 0.7459 0.8741
1.000 0.5003 0.00994 0.00511 -0.0863 0.7431 0.8752
1.250 0.5271 0.00989 0.00506 -0.0864 0.7407 0.8758
1.500 0.5553 0.00982 0.00498 -0.0868 0.7386 0.8764
1.750 0.5843 0.00974 0.00489 -0.0873 0.7367 0.8768
2.000 0.6137 0.00967 0.00480 -0.0880 0.7350 0.8774
2.250 0.6373 0.00970 0.00488 -0.0875 0.7317 0.8783
2.500 0.6626 0.00969 0.00490 -0.0873 0.7284 0.8790
2.750 0.6898 0.00964 0.00488 -0.0875 0.7254 0.8796
3.000 0.7182 0.00956 0.00481 -0.0879 0.7228 0.8802
3.250 0.7445 0.00953 0.00480 -0.0880 0.7195 0.8808
3.500 0.7680 0.00954 0.00488 -0.0875 0.7147 0.8816
3.750 0.7941 0.00949 0.00487 -0.0875 0.7105 0.8824
4.000 0.8202 0.00945 0.00487 -0.0874 0.7061 0.8833
4.250 0.8428 0.00947 0.00495 -0.0868 0.6990 0.8842
4.500 0.8679 0.00942 0.00493 -0.0865 0.6925 0.8849
4.750 0.8906 0.00941 0.00498 -0.0858 0.6834 0.8857
5.000 0.9127 0.00934 0.00490 -0.0849 0.6675 0.8864
5.250 0.9256 0.00933 0.00470 -0.0820 0.6278 0.8875
5.500 0.9221 0.00969 0.00482 -0.0759 0.5874 0.8891
5.750 0.9156 0.01032 0.00529 -0.0695 0.5521 0.8909
6.000 0.9141 0.01100 0.00585 -0.0645 0.5235 0.8927
6.250 0.9113 0.01183 0.00656 -0.0595 0.4920 0.8943
6.500 0.9056 0.01289 0.00744 -0.0543 0.4550 0.8961
6.750 0.9052 0.01389 0.00829 -0.0503 0.4204 0.8977
7.000 0.9057 0.01495 0.00918 -0.0465 0.3846 0.8992
7.250 0.9020 0.01625 0.01021 -0.0423 0.3327 0.9007
7.500 0.8907 0.01802 0.01150 -0.0373 0.2500 0.9023
7.750 0.8840 0.01966 0.01269 -0.0330 0.1684 0.9039
8.000 0.8721 0.02172 0.01418 -0.0282 0.0664 0.9054
8.250 0.8745 0.02312 0.01532 -0.0254 0.0170 0.9065
8.500 0.8895 0.02384 0.01606 -0.0242 0.0129 0.9074
8.750 0.9057 0.02449 0.01678 -0.0232 0.0117 0.9083
9.000 0.9205 0.02524 0.01758 -0.0221 0.0101 0.9092
9.250 0.9347 0.02605 0.01843 -0.0209 0.0089 0.9102
9.500 0.9471 0.02699 0.01946 -0.0196 0.0082 0.9112
9.750 0.9614 0.02783 0.02036 -0.0185 0.0079 0.9123
10.000 0.9748 0.02875 0.02134 -0.0174 0.0075 0.9133
10.250 0.9869 0.02978 0.02245 -0.0161 0.0071 0.9143
10.500 0.9985 0.03086 0.02362 -0.0149 0.0069 0.9154
10.750 1.0096 0.03202 0.02484 -0.0137 0.0065 0.9164
11.000 1.0204 0.03317 0.02604 -0.0126 0.0061 0.9176
11.250 1.0289 0.03452 0.02746 -0.0112 0.0058 0.9188
11.500 1.0305 0.03645 0.02948 -0.0093 0.0053 0.9201
11.750 1.0430 0.03756 0.03065 -0.0085 0.0051 0.9215
12.000 1.0511 0.03908 0.03227 -0.0073 0.0050 0.9230
12.250 1.0590 0.04065 0.03393 -0.0061 0.0048 0.9247
12.500 1.0677 0.04219 0.03556 -0.0052 0.0046 0.9265
12.750 1.0743 0.04396 0.03742 -0.0041 0.0044 0.9284
13.250 1.0876 0.04762 0.04131 -0.0022 0.0042 0.9320
13.500 1.0967 0.04923 0.04301 -0.0016 0.0039 0.9344
13.750 1.1031 0.05121 0.04509 -0.0008 0.0039 0.9367
14.000 1.1112 0.05307 0.04704 -0.0004 0.0037 0.9395
14.250 1.1179 0.05518 0.04926 0.0001 0.0037 0.9422
14.750 1.1325 0.05949 0.05377 0.0004 0.0035 0.9504
15.000 1.1388 0.06191 0.05631 0.0003 0.0034 0.9553
15.250 1.1449 0.06454 0.05907 0.0000 0.0033 0.9619
15.500 1.1501 0.06730 0.06197 -0.0003 0.0033 0.9725
15.750 1.1471 0.07069 0.06558 0.0005 0.0031 1.0000
16.000 1.1483 0.07385 0.06891 0.0004 0.0031 1.0000
16.250 1.1480 0.07728 0.07250 0.0001 0.0031 1.0000
16.500 1.1454 0.08114 0.07656 -0.0004 0.0030 1.0000
16.750 1.1411 0.08530 0.08089 -0.0011 0.0031 1.0000
17.000 1.1352 0.08980 0.08558 -0.0021 0.0030 1.0000
17.250 1.1276 0.09469 0.09065 -0.0035 0.0030 1.0000
17.500 1.1173 0.10018 0.09634 -0.0052 0.0030 1.0000
17.750 1.1061 0.10599 0.10235 -0.0074 0.0030 1.0000
18.000 1.0939 0.11216 0.10871 -0.0100 0.0030 1.0000
18.250 1.0804 0.11876 0.11550 -0.0131 0.0030 1.0000
18.500 1.0678 0.12538 0.12228 -0.0165 0.0030 1.0000
18.750 1.0526 0.13284 0.12991 -0.0205 0.0030 1.0000
19.000 1.0384 0.14034 0.13756 -0.0248 0.0030 1.0000
19.250 1.0195 0.14934 0.14675 -0.0301 0.0030 1.0000
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Polar data table (+)
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