A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 50,000 Max Cl/Cd: 44.47 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18sm-il-50000-n5.txt Download as CSV file: xf-a18sm-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4086 0.11424 0.10689 -0.0256 1.0000 0.0945
-8.750 -0.4021 0.11091 0.10358 -0.0256 1.0000 0.0965
-8.500 -0.4218 0.10673 0.09952 -0.0316 1.0000 0.0653
-8.250 -0.4110 0.10270 0.09549 -0.0302 1.0000 0.0643
-8.000 -0.4091 0.09950 0.09236 -0.0299 1.0000 0.0638
-7.750 -0.4087 0.09641 0.08934 -0.0298 1.0000 0.0631
-7.500 -0.4071 0.09313 0.08614 -0.0303 1.0000 0.0623
-7.250 -0.4052 0.08976 0.08284 -0.0312 1.0000 0.0612
-7.000 -0.4029 0.08617 0.07932 -0.0326 1.0000 0.0598
-6.750 -0.3997 0.08224 0.07545 -0.0349 1.0000 0.0582
-6.500 -0.3945 0.07779 0.07104 -0.0383 1.0000 0.0568
-5.750 -0.3463 0.05654 0.04941 -0.0610 1.0000 0.0528
-5.500 -0.3351 0.05600 0.04895 -0.0587 1.0000 0.0556
-5.250 -0.3129 0.05173 0.04450 -0.0625 1.0000 0.0588
-5.000 -0.2812 0.04509 0.03738 -0.0697 1.0000 0.0610
-4.750 -0.2454 0.03863 0.03016 -0.0760 1.0000 0.0627
-4.500 -0.2121 0.03417 0.02493 -0.0798 1.0000 0.0668
-4.250 -0.1869 0.03258 0.02314 -0.0804 1.0000 0.0733
-4.000 -0.1532 0.02928 0.01897 -0.0826 1.0000 0.0788
-3.750 -0.1281 0.02818 0.01780 -0.0828 1.0000 0.0868
-3.500 -0.1004 0.02681 0.01612 -0.0833 1.0000 0.0969
-3.250 -0.0728 0.02556 0.01456 -0.0835 1.0000 0.1079
-3.000 -0.0466 0.02484 0.01368 -0.0836 1.0000 0.1232
-2.750 -0.0201 0.02411 0.01283 -0.0837 1.0000 0.1394
-2.500 0.0065 0.02360 0.01216 -0.0838 1.0000 0.1613
-2.250 0.0334 0.02320 0.01173 -0.0840 1.0000 0.1847
-2.000 0.0602 0.02288 0.01133 -0.0842 1.0000 0.2115
-1.750 0.0865 0.02265 0.01111 -0.0843 1.0000 0.2425
-1.500 0.1127 0.02249 0.01095 -0.0845 1.0000 0.2779
-1.250 0.1387 0.02236 0.01094 -0.0847 1.0000 0.3179
-1.000 0.1710 0.02217 0.01089 -0.0862 0.9968 0.3730
-0.750 0.2105 0.02180 0.01084 -0.0890 0.9896 0.4580
-0.500 0.2470 0.02104 0.01082 -0.0907 0.9837 0.6316
-0.250 0.2784 0.02048 0.01053 -0.0914 0.9704 1.0000
0.000 0.3159 0.02074 0.01051 -0.0937 0.9597 1.0000
0.250 0.3528 0.02099 0.01055 -0.0959 0.9490 1.0000
0.500 0.3905 0.02124 0.01063 -0.0981 0.9388 1.0000
0.750 0.4303 0.02144 0.01071 -0.1007 0.9296 1.0000
1.000 0.4644 0.02165 0.01084 -0.1022 0.9177 1.0000
1.250 0.4989 0.02185 0.01100 -0.1036 0.9061 1.0000
1.500 0.5345 0.02203 0.01116 -0.1052 0.8951 1.0000
1.750 0.5728 0.02215 0.01127 -0.1072 0.8855 1.0000
2.000 0.6074 0.02227 0.01145 -0.1084 0.8743 1.0000
2.250 0.6392 0.02244 0.01167 -0.1091 0.8618 1.0000
2.500 0.6708 0.02260 0.01189 -0.1097 0.8494 1.0000
2.750 0.7027 0.02274 0.01213 -0.1103 0.8370 1.0000
3.000 0.7346 0.02288 0.01241 -0.1108 0.8245 1.0000
3.250 0.7664 0.02299 0.01265 -0.1112 0.8118 1.0000
3.500 0.7978 0.02310 0.01289 -0.1114 0.7985 1.0000
3.750 0.8282 0.02317 0.01312 -0.1112 0.7831 1.0000
4.000 0.8593 0.02297 0.01311 -0.1106 0.7632 1.0000
4.250 0.8880 0.02274 0.01301 -0.1093 0.7383 1.0000
4.500 0.9161 0.02257 0.01295 -0.1080 0.7120 1.0000
4.750 0.9434 0.02253 0.01305 -0.1067 0.6860 1.0000
5.000 0.9689 0.02260 0.01330 -0.1051 0.6569 1.0000
5.250 0.9927 0.02273 0.01355 -0.1033 0.6225 1.0000
5.500 1.0148 0.02291 0.01379 -0.1010 0.5795 1.0000
5.750 1.0335 0.02324 0.01405 -0.0982 0.5214 1.0000
6.000 1.0482 0.02388 0.01443 -0.0950 0.4370 1.0000
6.250 1.0579 0.02521 0.01513 -0.0915 0.3170 1.0000
6.500 1.0652 0.02735 0.01648 -0.0886 0.2206 1.0000
6.750 1.0755 0.02951 0.01822 -0.0864 0.1608 1.0000
7.000 1.0868 0.03160 0.02002 -0.0843 0.1226 1.0000
7.250 1.1003 0.03352 0.02191 -0.0822 0.0994 1.0000
7.500 1.1139 0.03537 0.02370 -0.0803 0.0839 1.0000
7.750 1.1309 0.03724 0.02576 -0.0784 0.0741 1.0000
8.000 1.1491 0.03915 0.02777 -0.0768 0.0658 1.0000
8.250 1.1672 0.04108 0.02973 -0.0755 0.0591 1.0000
8.500 1.1934 0.04358 0.03249 -0.0747 0.0549 1.0000
8.750 1.2145 0.04594 0.03514 -0.0736 0.0503 1.0000
9.000 1.2318 0.04848 0.03768 -0.0726 0.0465 1.0000
9.250 1.2498 0.05171 0.04142 -0.0711 0.0445 1.0000
9.500 1.2628 0.05532 0.04562 -0.0693 0.0431 1.0000
9.750 1.2698 0.05912 0.04991 -0.0670 0.0422 1.0000
10.000 1.2709 0.06299 0.05424 -0.0644 0.0414 1.0000
10.250 1.2667 0.06676 0.05842 -0.0616 0.0406 1.0000
10.500 1.2572 0.07037 0.06238 -0.0586 0.0399 1.0000
10.750 1.2433 0.07397 0.06626 -0.0556 0.0394 1.0000
11.000 1.2268 0.07795 0.07050 -0.0533 0.0390 1.0000
11.250 1.2070 0.08253 0.07536 -0.0521 0.0389 1.0000
11.500 1.1833 0.08807 0.08116 -0.0523 0.0392 1.0000
11.750 1.1563 0.09482 0.08815 -0.0543 0.0399 1.0000
12.000 1.1282 0.10287 0.09639 -0.0583 0.0408 1.0000
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Polar data table (+)
Polar graphs
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