A18 (original) (a18-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 100,000 Max Cl/Cd: 64.96 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18-il-100000.txt Download as CSV file: xf-a18-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4042 0.09641 0.09149 -0.0261 1.0000 0.0959
-8.500 -0.4199 0.09533 0.09055 -0.0300 1.0000 0.0980
-8.250 -0.4233 0.09192 0.08724 -0.0367 1.0000 0.0990
-8.000 -0.4103 0.08771 0.08299 -0.0271 1.0000 0.1019
-7.750 -0.4053 0.08515 0.08047 -0.0263 1.0000 0.1072
-7.500 -0.4016 0.08168 0.07698 -0.0445 1.0000 0.1126
-7.250 -0.4009 0.07852 0.07394 -0.0313 1.0000 0.1157
-7.000 -0.3939 0.07588 0.07132 -0.0305 1.0000 0.1214
-6.750 -0.3813 0.07097 0.06637 -0.0403 1.0000 0.1283
-6.500 -0.3543 0.06708 0.06222 -0.0520 1.0000 0.1412
-6.250 -0.3539 0.06361 0.05894 -0.0451 1.0000 0.1428
-6.000 -0.3474 0.06179 0.05718 -0.0407 1.0000 0.1504
-5.750 -0.3300 0.05811 0.05344 -0.0436 1.0000 0.1615
-5.500 -0.2421 0.03879 0.03256 -0.0735 1.0000 0.1123
-5.250 -0.2110 0.03386 0.02722 -0.0766 1.0000 0.1114
-5.000 -0.1855 0.03138 0.02457 -0.0776 1.0000 0.1167
-4.750 -0.1523 0.02821 0.02087 -0.0799 1.0000 0.1185
-4.500 -0.1206 0.02601 0.01815 -0.0815 1.0000 0.1224
-4.250 -0.0882 0.02429 0.01578 -0.0827 1.0000 0.1263
-4.000 -0.0579 0.02272 0.01400 -0.0837 1.0000 0.1295
-3.750 -0.0299 0.02186 0.01298 -0.0841 1.0000 0.1341
-3.500 -0.0016 0.02121 0.01204 -0.0844 1.0000 0.1421
-3.250 0.0255 0.02057 0.01140 -0.0847 1.0000 0.1490
-3.000 0.0535 0.02000 0.01068 -0.0850 1.0000 0.1570
-2.750 0.0805 0.01960 0.01029 -0.0853 1.0000 0.1682
-2.500 0.1070 0.01934 0.01011 -0.0856 1.0000 0.1865
-2.250 0.1336 0.01914 0.01002 -0.0859 1.0000 0.2143
-2.000 0.1633 0.01867 0.00984 -0.0869 1.0000 0.2679
-1.750 0.1906 0.01858 0.01015 -0.0875 1.0000 0.3451
-1.500 0.2220 0.01842 0.01034 -0.0889 0.9988 0.4421
-1.250 0.2576 0.01702 0.01039 -0.0897 0.9945 0.8639
-1.000 0.3048 0.01724 0.01029 -0.0943 0.9837 1.0000
-0.750 0.3486 0.01747 0.01033 -0.0980 0.9733 1.0000
-0.500 0.3921 0.01766 0.01038 -0.1014 0.9626 1.0000
-0.250 0.4361 0.01780 0.01042 -0.1049 0.9528 1.0000
0.000 0.4811 0.01786 0.01043 -0.1085 0.9438 1.0000
0.250 0.5194 0.01794 0.01050 -0.1107 0.9321 1.0000
0.500 0.5585 0.01798 0.01053 -0.1130 0.9210 1.0000
0.750 0.6031 0.01787 0.01044 -0.1162 0.9123 1.0000
1.000 0.6462 0.01764 0.01026 -0.1189 0.9018 1.0000
1.250 0.6857 0.01727 0.00994 -0.1204 0.8884 1.0000
1.500 0.7241 0.01680 0.00953 -0.1214 0.8741 1.0000
1.750 0.7595 0.01642 0.00925 -0.1219 0.8595 1.0000
2.000 0.7931 0.01610 0.00899 -0.1220 0.8444 1.0000
2.250 0.8243 0.01586 0.00881 -0.1216 0.8279 1.0000
2.500 0.8518 0.01579 0.00882 -0.1207 0.8088 1.0000
2.750 0.8805 0.01567 0.00879 -0.1199 0.7897 1.0000
3.000 0.9084 0.01557 0.00874 -0.1189 0.7692 1.0000
3.250 0.9344 0.01559 0.00883 -0.1177 0.7461 1.0000
3.500 0.9603 0.01566 0.00900 -0.1165 0.7225 1.0000
3.750 0.9846 0.01568 0.00904 -0.1147 0.6915 1.0000
4.000 1.0079 0.01571 0.00905 -0.1127 0.6543 1.0000
4.250 1.0302 0.01586 0.00918 -0.1108 0.6122 1.0000
4.500 1.0504 0.01617 0.00936 -0.1084 0.5562 1.0000
4.750 1.0658 0.01677 0.00967 -0.1054 0.4575 1.0000
5.000 1.0769 0.01812 0.01022 -0.1022 0.3198 1.0000
5.250 1.0860 0.02017 0.01141 -0.0994 0.2162 1.0000
5.500 1.0933 0.02280 0.01325 -0.0963 0.1141 1.0000
5.750 1.1051 0.02501 0.01516 -0.0933 0.0814 1.0000
6.000 1.1208 0.02686 0.01694 -0.0912 0.0690 1.0000
6.250 1.1388 0.02915 0.01908 -0.0896 0.0615 1.0000
6.500 1.1633 0.03108 0.02120 -0.0885 0.0576 1.0000
6.750 1.1883 0.03326 0.02351 -0.0877 0.0540 1.0000
7.000 1.2143 0.03701 0.02716 -0.0877 0.0498 1.0000
7.250 1.2358 0.03917 0.02977 -0.0862 0.0484 1.0000
7.500 1.2561 0.04237 0.03342 -0.0846 0.0479 1.0000
7.750 1.2724 0.04604 0.03761 -0.0827 0.0479 1.0000
8.000 1.2845 0.05022 0.04226 -0.0804 0.0483 1.0000
8.250 1.2929 0.05492 0.04737 -0.0781 0.0490 1.0000
8.500 1.2971 0.05974 0.05259 -0.0756 0.0493 1.0000
8.750 1.2989 0.06508 0.05826 -0.0732 0.0497 1.0000
9.000 1.2996 0.06922 0.06276 -0.0705 0.0501 1.0000
9.250 1.2537 0.07395 0.06860 -0.0627 0.0564 1.0000
9.500 1.2316 0.07843 0.07332 -0.0592 0.0579 1.0000
9.750 1.2122 0.08308 0.07812 -0.0569 0.0592 1.0000
10.000 1.1983 0.08820 0.08335 -0.0558 0.0603 1.0000
10.250 1.0426 0.08493 0.08044 -0.0415 0.0588 1.0000
10.500 1.0114 0.09123 0.08683 -0.0427 0.0593 1.0000
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Polar data table (+)
Polar graphs
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