A18 (original) (a18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 200,000 Max Cl/Cd: 80.68 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18-il-200000-n5.txt Download as CSV file: xf-a18-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: A18 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4443 0.08600 0.08254 -0.0313 1.0000 0.0145
-9.250 -0.4551 0.08249 0.07911 -0.0310 1.0000 0.0146
-9.000 -0.4655 0.07857 0.07527 -0.0315 1.0000 0.0146
-8.750 -0.4733 0.07371 0.07048 -0.0340 1.0000 0.0147
-8.500 -0.4792 0.06745 0.06427 -0.0388 1.0000 0.0148
-8.250 -0.4593 0.02683 0.02207 -0.0860 1.0000 0.0144
-8.000 -0.4310 0.02267 0.01722 -0.0892 1.0000 0.0159
-7.750 -0.4061 0.02145 0.01579 -0.0896 1.0000 0.0180
-7.500 -0.3775 0.02003 0.01405 -0.0906 0.9994 0.0206
-7.250 -0.3422 0.01853 0.01222 -0.0927 0.9976 0.0238
-7.000 -0.3070 0.01806 0.01158 -0.0945 0.9954 0.0298
-6.750 -0.2723 0.01798 0.01142 -0.0961 0.9924 0.0355
-6.500 -0.2369 0.01752 0.01068 -0.0979 0.9894 0.0415
-6.250 -0.2006 0.01752 0.01061 -0.0999 0.9866 0.0467
-6.000 -0.1662 0.01749 0.01033 -0.1012 0.9824 0.0517
-5.750 -0.1313 0.01659 0.00935 -0.1031 0.9792 0.0562
-5.500 -0.0951 0.01593 0.00852 -0.1050 0.9767 0.0586
-5.250 -0.0624 0.01542 0.00788 -0.1061 0.9720 0.0619
-5.000 -0.0272 0.01483 0.00715 -0.1077 0.9682 0.0642
-4.750 0.0096 0.01429 0.00647 -0.1095 0.9655 0.0659
-4.500 0.0415 0.01368 0.00582 -0.1105 0.9601 0.0683
-4.250 0.0754 0.01323 0.00535 -0.1118 0.9560 0.0714
-4.000 0.1105 0.01285 0.00493 -0.1134 0.9527 0.0751
-3.750 0.1409 0.01257 0.00458 -0.1138 0.9461 0.0790
-3.500 0.1742 0.01222 0.00426 -0.1150 0.9410 0.0858
-3.250 0.2073 0.01194 0.00398 -0.1161 0.9359 0.0956
-3.000 0.2383 0.01166 0.00376 -0.1168 0.9285 0.1106
-2.750 0.2721 0.01138 0.00355 -0.1180 0.9230 0.1373
-2.500 0.3022 0.01115 0.00341 -0.1184 0.9139 0.1675
-2.250 0.3340 0.01091 0.00331 -0.1192 0.9060 0.2056
-2.000 0.3650 0.01074 0.00319 -0.1198 0.8974 0.2397
-1.750 0.3950 0.01055 0.00310 -0.1202 0.8879 0.2694
-1.500 0.4255 0.01032 0.00308 -0.1208 0.8783 0.3263
-1.250 0.4552 0.01014 0.00305 -0.1211 0.8675 0.3978
-1.000 0.4838 0.00984 0.00304 -0.1212 0.8554 0.4684
-0.750 0.5113 0.00951 0.00306 -0.1210 0.8421 0.5870
-0.500 0.5352 0.00905 0.00303 -0.1197 0.8280 0.7506
-0.250 0.5594 0.00868 0.00287 -0.1183 0.8135 1.0000
0.000 0.5876 0.00876 0.00283 -0.1181 0.7958 1.0000
0.250 0.6150 0.00887 0.00283 -0.1177 0.7742 1.0000
0.500 0.6424 0.00900 0.00284 -0.1174 0.7528 1.0000
0.750 0.6695 0.00914 0.00290 -0.1171 0.7313 1.0000
1.000 0.6965 0.00931 0.00296 -0.1167 0.7101 1.0000
1.250 0.7235 0.00949 0.00308 -0.1164 0.6897 1.0000
1.500 0.7503 0.00967 0.00320 -0.1161 0.6678 1.0000
1.750 0.7769 0.00988 0.00333 -0.1157 0.6449 1.0000
2.000 0.8032 0.01010 0.00350 -0.1153 0.6214 1.0000
2.250 0.8295 0.01034 0.00368 -0.1150 0.5990 1.0000
2.500 0.8553 0.01062 0.00388 -0.1145 0.5747 1.0000
2.750 0.8810 0.01092 0.00413 -0.1140 0.5515 1.0000
3.000 0.9061 0.01127 0.00440 -0.1135 0.5231 1.0000
3.250 0.9306 0.01165 0.00468 -0.1128 0.4795 1.0000
3.500 0.9524 0.01225 0.00496 -0.1118 0.4165 1.0000
3.750 0.9755 0.01282 0.00541 -0.1110 0.3763 1.0000
4.000 0.9928 0.01405 0.00597 -0.1095 0.2441 1.0000
4.250 1.0127 0.01509 0.00667 -0.1085 0.1843 1.0000
4.500 1.0353 0.01578 0.00723 -0.1078 0.1504 1.0000
4.750 1.0573 0.01652 0.00778 -0.1071 0.1063 1.0000
5.000 1.0767 0.01761 0.00855 -0.1060 0.0570 1.0000
5.250 1.0964 0.01869 0.00950 -0.1047 0.0291 1.0000
5.500 1.1174 0.01960 0.01042 -0.1036 0.0222 1.0000
5.750 1.1387 0.02042 0.01137 -0.1025 0.0191 1.0000
6.000 1.1585 0.02142 0.01245 -0.1012 0.0162 1.0000
6.250 1.1746 0.02285 0.01404 -0.0993 0.0146 1.0000
6.500 1.1923 0.02402 0.01534 -0.0976 0.0139 1.0000
6.750 1.2095 0.02525 0.01671 -0.0960 0.0133 1.0000
7.000 1.2269 0.02649 0.01814 -0.0943 0.0125 1.0000
7.250 1.2443 0.02768 0.01945 -0.0928 0.0114 1.0000
7.500 1.2608 0.02898 0.02086 -0.0912 0.0107 1.0000
7.750 1.2761 0.03054 0.02255 -0.0894 0.0102 1.0000
8.000 1.2905 0.03232 0.02447 -0.0876 0.0098 1.0000
8.250 1.3036 0.03452 0.02684 -0.0857 0.0095 1.0000
8.500 1.3151 0.03746 0.03001 -0.0836 0.0092 1.0000
8.750 1.3252 0.04029 0.03313 -0.0814 0.0090 1.0000
9.000 1.3333 0.04266 0.03580 -0.0788 0.0089 1.0000
9.250 1.3375 0.04499 0.03845 -0.0759 0.0087 1.0000
9.500 1.3364 0.04725 0.04101 -0.0723 0.0085 1.0000
9.750 1.3326 0.04975 0.04381 -0.0687 0.0083 1.0000
10.000 1.3263 0.05252 0.04687 -0.0654 0.0081 1.0000
10.250 1.3179 0.05553 0.05016 -0.0626 0.0078 1.0000
10.500 1.3064 0.05910 0.05400 -0.0603 0.0077 1.0000
10.750 1.2937 0.06296 0.05813 -0.0587 0.0076 1.0000
11.000 1.2783 0.06751 0.06293 -0.0580 0.0075 1.0000
11.250 1.2608 0.07275 0.06842 -0.0583 0.0075 1.0000
11.500 1.2421 0.07869 0.07460 -0.0597 0.0075 1.0000
11.750 1.2217 0.08555 0.08168 -0.0624 0.0075 1.0000
12.000 1.2003 0.09339 0.08973 -0.0664 0.0076 1.0000
12.250 1.1776 0.10243 0.09897 -0.0717 0.0077 1.0000
12.500 1.1540 0.11286 0.10957 -0.0783 0.0079 1.0000
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Polar data table (+)
Polar graphs
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