A18 (original) (a18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 200,000 Max Cl/Cd: 86.33 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18-il-200000.txt Download as CSV file: xf-a18-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4122 0.08816 0.08474 -0.0260 1.0000 0.0519
-8.250 -0.4158 0.08549 0.08213 -0.0263 1.0000 0.0535
-8.000 -0.4189 0.08229 0.07899 -0.0297 1.0000 0.0561
-7.750 -0.4124 0.07714 0.07385 -0.0414 1.0000 0.0576
-7.500 -0.4001 0.07155 0.06820 -0.0483 1.0000 0.0579
-7.250 -0.4075 0.06823 0.06499 -0.0419 1.0000 0.0596
-7.000 -0.4011 0.06638 0.06313 -0.0395 1.0000 0.0610
-6.750 -0.3573 0.04329 0.03945 -0.0664 1.0000 0.0448
-6.500 -0.3167 0.03147 0.02646 -0.0777 1.0000 0.0457
-6.250 -0.2968 0.02963 0.02474 -0.0783 1.0000 0.0498
-6.000 -0.2653 0.02580 0.02028 -0.0809 1.0000 0.0542
-5.750 -0.2336 0.02270 0.01651 -0.0830 1.0000 0.0605
-5.500 -0.2104 0.02225 0.01604 -0.0827 1.0000 0.0657
-5.250 -0.1830 0.02161 0.01492 -0.0828 1.0000 0.0710
-5.000 -0.1527 0.01976 0.01293 -0.0842 1.0000 0.0763
-4.750 -0.1263 0.01923 0.01222 -0.0843 1.0000 0.0812
-4.500 -0.0858 0.01836 0.01098 -0.0869 0.9973 0.0844
-4.250 -0.0460 0.01717 0.00973 -0.0897 0.9953 0.0897
-4.000 -0.0062 0.01652 0.00894 -0.0922 0.9921 0.0939
-3.750 0.0336 0.01597 0.00825 -0.0946 0.9882 0.0981
-3.500 0.0741 0.01526 0.00758 -0.0974 0.9854 0.1044
-3.250 0.1142 0.01491 0.00717 -0.1000 0.9820 0.1131
-3.000 0.1511 0.01442 0.00677 -0.1020 0.9768 0.1239
-2.750 0.1916 0.01394 0.00639 -0.1047 0.9732 0.1436
-2.500 0.2341 0.01342 0.00613 -0.1080 0.9706 0.1975
-2.250 0.2687 0.01306 0.00597 -0.1096 0.9632 0.2583
-2.000 0.3097 0.01264 0.00586 -0.1125 0.9592 0.3288
-1.750 0.3494 0.01229 0.00571 -0.1150 0.9540 0.4060
-1.500 0.3868 0.01171 0.00560 -0.1171 0.9478 0.5153
-1.250 0.4184 0.01039 0.00536 -0.1170 0.9439 1.0000
-1.000 0.4520 0.01031 0.00518 -0.1180 0.9352 1.0000
-0.750 0.4906 0.01013 0.00492 -0.1200 0.9298 1.0000
-0.500 0.5224 0.01002 0.00476 -0.1204 0.9195 1.0000
-0.250 0.5557 0.00987 0.00456 -0.1212 0.9102 1.0000
0.000 0.5885 0.00967 0.00432 -0.1217 0.8996 1.0000
0.250 0.6174 0.00954 0.00414 -0.1213 0.8845 1.0000
0.500 0.6453 0.00946 0.00402 -0.1207 0.8679 1.0000
0.750 0.6731 0.00943 0.00397 -0.1202 0.8513 1.0000
1.000 0.7007 0.00944 0.00393 -0.1197 0.8339 1.0000
1.250 0.7282 0.00947 0.00391 -0.1192 0.8160 1.0000
1.500 0.7552 0.00956 0.00397 -0.1186 0.7965 1.0000
1.750 0.7819 0.00967 0.00404 -0.1181 0.7760 1.0000
2.000 0.8086 0.00981 0.00412 -0.1175 0.7553 1.0000
2.250 0.8349 0.00998 0.00426 -0.1169 0.7336 1.0000
2.500 0.8613 0.01018 0.00442 -0.1163 0.7124 1.0000
2.750 0.8871 0.01038 0.00459 -0.1157 0.6874 1.0000
3.000 0.9123 0.01059 0.00475 -0.1148 0.6578 1.0000
3.250 0.9367 0.01085 0.00491 -0.1139 0.6223 1.0000
3.500 0.9610 0.01116 0.00514 -0.1130 0.5871 1.0000
3.750 0.9844 0.01157 0.00541 -0.1119 0.5469 1.0000
4.000 1.0065 0.01207 0.00572 -0.1107 0.4893 1.0000
4.250 1.0245 0.01292 0.00607 -0.1088 0.3986 1.0000
4.500 1.0407 0.01416 0.00669 -0.1071 0.2661 1.0000
4.750 1.0592 0.01532 0.00750 -0.1058 0.2055 1.0000
5.000 1.0792 0.01633 0.00826 -0.1047 0.1525 1.0000
5.250 1.0915 0.01847 0.00968 -0.1024 0.0562 1.0000
5.500 1.1095 0.01984 0.01105 -0.1005 0.0441 1.0000
5.750 1.1245 0.02151 0.01272 -0.0984 0.0387 1.0000
6.000 1.1455 0.02242 0.01376 -0.0971 0.0351 1.0000
6.250 1.1645 0.02359 0.01498 -0.0956 0.0322 1.0000
6.500 1.1818 0.02529 0.01669 -0.0939 0.0303 1.0000
6.750 1.2011 0.02803 0.01948 -0.0925 0.0290 1.0000
7.000 1.2239 0.02975 0.02138 -0.0914 0.0284 1.0000
7.250 1.2459 0.03139 0.02324 -0.0903 0.0272 1.0000
7.500 1.2666 0.03312 0.02521 -0.0891 0.0257 1.0000
7.750 1.2866 0.03565 0.02803 -0.0877 0.0252 1.0000
8.000 1.3038 0.03877 0.03153 -0.0859 0.0252 1.0000
8.250 1.3162 0.04256 0.03579 -0.0835 0.0256 1.0000
8.500 1.3228 0.04698 0.04069 -0.0805 0.0265 1.0000
8.750 1.3238 0.05181 0.04595 -0.0773 0.0276 1.0000
9.000 1.3349 0.05695 0.05125 -0.0756 0.0299 1.0000
13.000 0.7911 0.16026 0.15727 -0.0786 0.0589 1.0000
13.250 0.7855 0.16428 0.16129 -0.0806 0.0566 1.0000
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Polar data table (+)
Polar graphs
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