A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 50,000 Max Cl/Cd: 44.24 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18sm-il-50000.txt Download as CSV file: xf-a18sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: A18 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4192 0.10716 0.10034 -0.0226 1.0000 0.1912
-7.500 -0.3925 0.10053 0.09364 -0.0204 1.0000 0.2005
-7.250 -0.4112 0.10066 0.09397 -0.0217 1.0000 0.2053
-7.000 -0.3954 0.09545 0.08875 -0.0190 1.0000 0.2117
-6.750 -0.4054 0.09464 0.08809 -0.0216 1.0000 0.2197
-6.250 -0.4009 0.08898 0.08258 -0.0231 1.0000 0.2351
-6.000 -0.3890 0.08463 0.07821 -0.0185 1.0000 0.2439
-5.750 -0.3862 0.08176 0.07542 -0.0187 1.0000 0.2543
-5.500 -0.3821 0.07898 0.07270 -0.0186 1.0000 0.2682
-5.250 -0.3767 0.07614 0.06991 -0.0177 1.0000 0.2839
-5.000 -0.3705 0.07330 0.06712 -0.0172 1.0000 0.3003
-4.750 -0.3623 0.07089 0.06473 -0.0207 1.0000 0.3222
-4.500 -0.3545 0.06756 0.06144 -0.0185 1.0000 0.3381
-4.250 -0.3459 0.06450 0.05842 -0.0163 1.0000 0.3562
-4.000 -0.2166 0.04629 0.03864 -0.0666 1.0000 0.1768
-3.750 -0.1885 0.04203 0.03421 -0.0687 1.0000 0.1716
-3.500 -0.1406 0.03593 0.02723 -0.0762 1.0000 0.1652
-3.250 -0.1054 0.03297 0.02362 -0.0790 1.0000 0.1776
-3.000 -0.0746 0.03060 0.02096 -0.0802 1.0000 0.1872
-2.750 -0.0442 0.02888 0.01892 -0.0813 1.0000 0.2083
-2.500 -0.0146 0.02732 0.01713 -0.0820 1.0000 0.2275
-2.250 0.0136 0.02626 0.01593 -0.0823 1.0000 0.2570
-2.000 0.0429 0.02529 0.01478 -0.0828 1.0000 0.2899
-1.750 0.0707 0.02450 0.01396 -0.0831 1.0000 0.3263
-1.500 0.0983 0.02391 0.01336 -0.0832 1.0000 0.3708
-1.250 0.1264 0.02335 0.01282 -0.0834 1.0000 0.4244
-1.000 0.1546 0.02272 0.01235 -0.0836 1.0000 0.4945
-0.750 0.1826 0.02170 0.01195 -0.0834 1.0000 0.6134
-0.500 0.1909 0.02046 0.01141 -0.0797 1.0000 1.0000
-0.250 0.2177 0.02101 0.01142 -0.0806 1.0000 1.0000
0.000 0.2411 0.02160 0.01169 -0.0808 1.0000 1.0000
0.250 0.2635 0.02225 0.01212 -0.0809 1.0000 1.0000
0.500 0.2852 0.02296 0.01266 -0.0810 1.0000 1.0000
0.750 0.3063 0.02373 0.01329 -0.0811 1.0000 1.0000
1.000 0.3268 0.02457 0.01403 -0.0812 1.0000 1.0000
1.250 0.3467 0.02549 0.01486 -0.0814 1.0000 1.0000
1.500 0.3661 0.02647 0.01578 -0.0815 1.0000 1.0000
1.750 0.3851 0.02752 0.01678 -0.0817 1.0000 1.0000
2.000 0.4035 0.02863 0.01788 -0.0820 1.0000 1.0000
2.250 0.4374 0.02984 0.01908 -0.0851 0.9935 1.0000
2.500 0.4828 0.03099 0.02026 -0.0902 0.9787 1.0000
2.750 0.5264 0.03209 0.02141 -0.0947 0.9639 1.0000
3.000 0.5684 0.03313 0.02255 -0.0987 0.9489 1.0000
3.250 0.6096 0.03411 0.02364 -0.1024 0.9337 1.0000
3.500 0.6510 0.03501 0.02467 -0.1059 0.9181 1.0000
3.750 0.6946 0.03577 0.02564 -0.1095 0.9021 1.0000
4.000 0.7282 0.03647 0.02652 -0.1111 0.8826 1.0000
4.250 0.7783 0.03650 0.02679 -0.1143 0.8610 1.0000
4.500 0.8216 0.03625 0.02686 -0.1158 0.8360 1.0000
4.750 0.8727 0.03534 0.02630 -0.1174 0.8113 1.0000
5.000 0.9369 0.03314 0.02455 -0.1193 0.7875 1.0000
5.250 0.9857 0.03106 0.02292 -0.1183 0.7592 1.0000
5.500 1.0245 0.02900 0.02121 -0.1152 0.7225 1.0000
5.750 1.0620 0.02628 0.01872 -0.1103 0.6707 1.0000
6.000 1.0822 0.02475 0.01722 -0.1039 0.5954 1.0000
6.250 1.0883 0.02460 0.01652 -0.0962 0.4654 1.0000
6.500 1.0834 0.02720 0.01752 -0.0893 0.2974 1.0000
6.750 1.0928 0.03084 0.02005 -0.0860 0.2078 1.0000
7.000 1.1177 0.03401 0.02271 -0.0849 0.1631 1.0000
7.250 1.1472 0.03686 0.02554 -0.0842 0.1389 1.0000
7.500 1.1764 0.04001 0.02852 -0.0841 0.1227 1.0000
7.750 1.2007 0.04293 0.03204 -0.0826 0.1139 1.0000
8.000 1.2258 0.04677 0.03604 -0.0819 0.1081 1.0000
8.250 1.2406 0.05007 0.04004 -0.0795 0.1032 1.0000
8.500 1.2570 0.05359 0.04387 -0.0778 0.0989 1.0000
8.750 1.2687 0.05794 0.04872 -0.0756 0.0983 1.0000
9.000 1.2711 0.06267 0.05413 -0.0725 0.0993 1.0000
9.250 1.2668 0.06780 0.05989 -0.0694 0.1013 1.0000
9.500 1.2574 0.07304 0.06561 -0.0665 0.1035 1.0000
9.750 1.2473 0.07825 0.07117 -0.0640 0.1056 1.0000
10.000 1.2390 0.08355 0.07670 -0.0621 0.1074 1.0000
10.250 1.2397 0.08942 0.08266 -0.0610 0.1089 1.0000
10.500 1.1733 0.09346 0.08717 -0.0579 0.1126 1.0000
10.750 1.1285 0.10072 0.09457 -0.0602 0.1151 1.0000
11.000 1.0969 0.10944 0.10334 -0.0649 0.1186 1.0000
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Polar data table (+)
Polar graphs
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