A18 (original) (a18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 500,000 Max Cl/Cd: 111.88 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18-il-500000.txt Download as CSV file: xf-a18-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4139 0.09993 0.09759 -0.0270 1.0000 0.0254
-9.750 -0.4171 0.09608 0.09377 -0.0302 1.0000 0.0266
-9.000 -0.5381 0.02452 0.02100 -0.0866 1.0000 0.0146
-8.750 -0.5136 0.02169 0.01769 -0.0882 1.0000 0.0152
-8.500 -0.4879 0.01864 0.01421 -0.0899 1.0000 0.0166
-8.250 -0.4640 0.01789 0.01334 -0.0896 1.0000 0.0176
-8.000 -0.4384 0.01685 0.01208 -0.0897 0.9999 0.0187
-7.750 -0.4031 0.01579 0.01077 -0.0916 0.9987 0.0200
-7.500 -0.3678 0.01441 0.00918 -0.0937 0.9975 0.0224
-7.250 -0.3315 0.01419 0.00891 -0.0955 0.9958 0.0252
-7.000 -0.2951 0.01353 0.00813 -0.0975 0.9947 0.0291
-6.750 -0.2599 0.01357 0.00816 -0.0989 0.9925 0.0333
-6.500 -0.2252 0.01309 0.00759 -0.1005 0.9903 0.0380
-6.250 -0.1895 0.01325 0.00775 -0.1022 0.9879 0.0423
-6.000 -0.1528 0.01336 0.00777 -0.1039 0.9859 0.0454
-5.750 -0.1164 0.01235 0.00667 -0.1060 0.9847 0.0497
-5.500 -0.0790 0.01216 0.00645 -0.1081 0.9834 0.0534
-5.250 -0.0470 0.01196 0.00617 -0.1089 0.9794 0.0565
-5.000 -0.0121 0.01144 0.00557 -0.1105 0.9767 0.0590
-4.750 0.0240 0.01071 0.00481 -0.1123 0.9748 0.0623
-4.500 0.0610 0.01035 0.00443 -0.1143 0.9731 0.0657
-4.250 0.0985 0.00998 0.00402 -0.1163 0.9717 0.0686
-4.000 0.1330 0.00970 0.00369 -0.1177 0.9688 0.0708
-3.750 0.1647 0.00922 0.00322 -0.1185 0.9637 0.0757
-3.500 0.1985 0.00893 0.00294 -0.1197 0.9600 0.0812
-3.250 0.2328 0.00864 0.00265 -0.1209 0.9567 0.0891
-3.000 0.2614 0.00838 0.00246 -0.1210 0.9488 0.1036
-2.750 0.2932 0.00805 0.00228 -0.1217 0.9434 0.1440
-2.500 0.3215 0.00783 0.00219 -0.1217 0.9344 0.1847
-2.250 0.3509 0.00766 0.00211 -0.1219 0.9262 0.2206
-2.000 0.3792 0.00750 0.00201 -0.1218 0.9158 0.2505
-1.750 0.4071 0.00732 0.00195 -0.1217 0.9044 0.2893
-1.500 0.4350 0.00718 0.00196 -0.1216 0.8926 0.3580
-1.250 0.4626 0.00710 0.00192 -0.1213 0.8786 0.3961
-1.000 0.4899 0.00700 0.00187 -0.1211 0.8620 0.4298
-0.750 0.5172 0.00676 0.00190 -0.1209 0.8446 0.5328
-0.500 0.5402 0.00602 0.00198 -0.1197 0.8276 0.8154
-0.250 0.5633 0.00578 0.00185 -0.1181 0.8081 1.0000
0.000 0.5907 0.00590 0.00185 -0.1179 0.7887 1.0000
0.250 0.6182 0.00602 0.00187 -0.1176 0.7705 1.0000
0.500 0.6457 0.00615 0.00191 -0.1174 0.7512 1.0000
0.750 0.6730 0.00630 0.00198 -0.1172 0.7310 1.0000
1.000 0.7001 0.00646 0.00204 -0.1170 0.7086 1.0000
1.250 0.7273 0.00663 0.00212 -0.1168 0.6873 1.0000
1.500 0.7545 0.00680 0.00222 -0.1166 0.6655 1.0000
2.000 0.8078 0.00722 0.00244 -0.1160 0.6116 1.0000
2.250 0.8339 0.00750 0.00258 -0.1156 0.5803 1.0000
2.500 0.8598 0.00781 0.00277 -0.1153 0.5502 1.0000
2.750 0.8855 0.00814 0.00297 -0.1149 0.5163 1.0000
3.000 0.9113 0.00845 0.00315 -0.1145 0.4699 1.0000
3.250 0.9346 0.00906 0.00340 -0.1138 0.4070 1.0000
3.500 0.9591 0.00958 0.00374 -0.1134 0.3541 1.0000
3.750 0.9791 0.01072 0.00425 -0.1124 0.2283 1.0000
4.000 1.0028 0.01138 0.00469 -0.1119 0.1866 1.0000
4.250 1.0274 0.01188 0.00507 -0.1114 0.1571 1.0000
4.500 1.0518 0.01241 0.00546 -0.1110 0.1209 1.0000
4.750 1.0714 0.01359 0.00618 -0.1099 0.0475 1.0000
5.000 1.0934 0.01446 0.00692 -0.1089 0.0263 1.0000
5.250 1.1156 0.01529 0.00777 -0.1079 0.0214 1.0000
5.500 1.1392 0.01587 0.00842 -0.1071 0.0200 1.0000
5.750 1.1618 0.01655 0.00919 -0.1062 0.0185 1.0000
6.000 1.1834 0.01734 0.01003 -0.1052 0.0172 1.0000
6.250 1.1995 0.01882 0.01160 -0.1032 0.0156 1.0000
6.500 1.2199 0.01972 0.01259 -0.1020 0.0149 1.0000
6.750 1.2399 0.02066 0.01363 -0.1006 0.0144 1.0000
7.000 1.2592 0.02174 0.01480 -0.0992 0.0138 1.0000
7.250 1.2779 0.02291 0.01608 -0.0978 0.0133 1.0000
7.500 1.2965 0.02417 0.01743 -0.0963 0.0128 1.0000
7.750 1.3147 0.02554 0.01890 -0.0948 0.0124 1.0000
8.000 1.3324 0.02706 0.02054 -0.0933 0.0120 1.0000
8.250 1.3492 0.02880 0.02237 -0.0918 0.0116 1.0000
8.500 1.3627 0.03249 0.02627 -0.0900 0.0111 1.0000
8.750 1.3746 0.03492 0.02901 -0.0878 0.0108 1.0000
9.000 1.3861 0.03694 0.03130 -0.0855 0.0106 1.0000
9.250 1.3939 0.03946 0.03411 -0.0828 0.0106 1.0000
9.500 1.3976 0.04215 0.03710 -0.0797 0.0105 1.0000
9.750 1.3952 0.04528 0.04052 -0.0760 0.0105 1.0000
10.000 1.3853 0.04838 0.04389 -0.0713 0.0105 1.0000
10.250 1.3705 0.05178 0.04755 -0.0666 0.0106 1.0000
10.500 1.2597 0.04795 0.04393 -0.0501 0.0110 1.0000
10.750 1.2392 0.05191 0.04810 -0.0469 0.0110 1.0000
11.000 1.2222 0.05559 0.05194 -0.0446 0.0111 1.0000
11.250 1.2051 0.05948 0.05599 -0.0430 0.0111 1.0000
11.500 1.1841 0.06428 0.06096 -0.0420 0.0112 1.0000
11.750 1.1598 0.06986 0.06671 -0.0417 0.0112 1.0000
12.000 1.1391 0.07508 0.07208 -0.0421 0.0113 1.0000
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Polar data table (+)
Polar graphs
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