A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 500,000 Max Cl/Cd: 114.94 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18sm-il-500000.txt Download as CSV file: xf-a18sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4107 0.09116 0.08891 -0.0308 1.0000 0.0224
-8.000 -0.4198 0.08881 0.08661 -0.0290 1.0000 0.0224
-7.750 -0.4427 0.08367 0.08155 -0.0279 1.0000 0.0231
-7.500 -0.4453 0.08125 0.07917 -0.0272 1.0000 0.0233
-7.250 -0.4468 0.07882 0.07675 -0.0269 1.0000 0.0236
-7.000 -0.4467 0.07623 0.07419 -0.0271 1.0000 0.0239
-6.750 -0.3980 0.03089 0.02785 -0.0812 0.9963 0.0163
-6.500 -0.3587 0.02269 0.01866 -0.0896 0.9953 0.0164
-6.250 -0.3227 0.01871 0.01409 -0.0934 0.9946 0.0171
-6.000 -0.2881 0.01711 0.01225 -0.0956 0.9931 0.0179
-5.750 -0.2536 0.01605 0.01101 -0.0974 0.9911 0.0189
-5.500 -0.2183 0.01527 0.01006 -0.0993 0.9891 0.0205
-5.250 -0.1821 0.01436 0.00895 -0.1011 0.9874 0.0219
-5.000 -0.1458 0.01275 0.00709 -0.1032 0.9863 0.0243
-4.750 -0.1088 0.01220 0.00649 -0.1053 0.9849 0.0273
-4.500 -0.0713 0.01182 0.00601 -0.1074 0.9837 0.0304
-4.250 -0.0380 0.01108 0.00523 -0.1087 0.9807 0.0360
-4.000 -0.0036 0.01079 0.00488 -0.1101 0.9776 0.0406
-3.750 0.0326 0.01023 0.00431 -0.1120 0.9754 0.0496
-3.500 0.0698 0.00980 0.00388 -0.1140 0.9737 0.0605
-3.250 0.1076 0.00946 0.00357 -0.1162 0.9723 0.0758
-3.000 0.1457 0.00914 0.00328 -0.1184 0.9710 0.0942
-2.750 0.1772 0.00888 0.00309 -0.1192 0.9660 0.1133
-2.500 0.2110 0.00865 0.00289 -0.1204 0.9620 0.1333
-2.250 0.2458 0.00838 0.00270 -0.1218 0.9587 0.1557
-2.000 0.2764 0.00818 0.00254 -0.1223 0.9529 0.1777
-1.750 0.3073 0.00796 0.00240 -0.1228 0.9465 0.2043
-1.500 0.3371 0.00776 0.00228 -0.1231 0.9397 0.2337
-1.250 0.3661 0.00755 0.00218 -0.1232 0.9314 0.2704
-1.000 0.3941 0.00738 0.00212 -0.1231 0.9218 0.3130
-0.750 0.4224 0.00720 0.00206 -0.1230 0.9121 0.3621
-0.500 0.4504 0.00703 0.00201 -0.1229 0.9015 0.4160
-0.250 0.4778 0.00682 0.00200 -0.1227 0.8890 0.4888
0.000 0.5048 0.00649 0.00202 -0.1224 0.8760 0.6202
0.250 0.5253 0.00562 0.00192 -0.1202 0.8620 1.0000
0.500 0.5529 0.00568 0.00190 -0.1200 0.8473 1.0000
0.750 0.5806 0.00576 0.00188 -0.1197 0.8320 1.0000
1.000 0.6081 0.00585 0.00189 -0.1194 0.8158 1.0000
1.250 0.6355 0.00595 0.00191 -0.1191 0.7973 1.0000
1.500 0.6621 0.00610 0.00193 -0.1186 0.7726 1.0000
1.750 0.6885 0.00627 0.00196 -0.1181 0.7441 1.0000
2.000 0.7151 0.00645 0.00202 -0.1177 0.7185 1.0000
2.250 0.7421 0.00662 0.00210 -0.1174 0.6965 1.0000
2.500 0.7690 0.00680 0.00221 -0.1171 0.6758 1.0000
2.750 0.7960 0.00698 0.00232 -0.1168 0.6550 1.0000
3.000 0.8227 0.00718 0.00244 -0.1165 0.6333 1.0000
3.250 0.8494 0.00739 0.00257 -0.1161 0.6097 1.0000
3.500 0.8755 0.00764 0.00273 -0.1157 0.5813 1.0000
3.750 0.9010 0.00794 0.00290 -0.1152 0.5472 1.0000
4.000 0.9267 0.00823 0.00308 -0.1148 0.5136 1.0000
4.250 0.9518 0.00860 0.00330 -0.1142 0.4723 1.0000
4.500 0.9759 0.00909 0.00357 -0.1135 0.4160 1.0000
4.750 0.9976 0.00990 0.00395 -0.1126 0.3236 1.0000
5.000 1.0172 0.01105 0.00454 -0.1115 0.2172 1.0000
5.250 1.0395 0.01186 0.00504 -0.1107 0.1582 1.0000
5.500 1.0625 0.01255 0.00550 -0.1100 0.1145 1.0000
5.750 1.0845 0.01335 0.00606 -0.1091 0.0706 1.0000
6.000 1.1065 0.01414 0.00671 -0.1081 0.0440 1.0000
6.250 1.1291 0.01487 0.00741 -0.1071 0.0332 1.0000
6.500 1.1502 0.01575 0.00829 -0.1059 0.0264 1.0000
6.750 1.1732 0.01634 0.00896 -0.1050 0.0241 1.0000
7.000 1.1954 0.01701 0.00970 -0.1039 0.0219 1.0000
7.250 1.2159 0.01786 0.01060 -0.1026 0.0201 1.0000
7.500 1.2289 0.01969 0.01256 -0.1000 0.0185 1.0000
7.750 1.2513 0.02024 0.01319 -0.0990 0.0178 1.0000
8.000 1.2721 0.02099 0.01401 -0.0978 0.0167 1.0000
8.250 1.2912 0.02196 0.01508 -0.0963 0.0159 1.0000
8.500 1.3098 0.02300 0.01621 -0.0948 0.0151 1.0000
8.750 1.3279 0.02408 0.01738 -0.0932 0.0145 1.0000
9.000 1.3445 0.02542 0.01879 -0.0915 0.0139 1.0000
9.250 1.3568 0.02828 0.02182 -0.0892 0.0131 1.0000
9.500 1.3729 0.02992 0.02367 -0.0874 0.0125 1.0000
9.750 1.3896 0.03095 0.02485 -0.0857 0.0120 1.0000
10.000 1.4038 0.03266 0.02676 -0.0837 0.0116 1.0000
10.250 1.4157 0.03461 0.02893 -0.0814 0.0112 1.0000
10.500 1.4251 0.03664 0.03120 -0.0788 0.0108 1.0000
10.750 1.4310 0.03879 0.03357 -0.0759 0.0106 1.0000
11.000 1.4323 0.04090 0.03589 -0.0723 0.0104 1.0000
11.250 1.4305 0.04298 0.03815 -0.0685 0.0102 1.0000
11.500 1.4259 0.04533 0.04070 -0.0648 0.0100 1.0000
11.750 1.4181 0.04809 0.04368 -0.0612 0.0099 1.0000
12.000 1.4090 0.05100 0.04680 -0.0582 0.0098 1.0000
12.250 1.3956 0.05463 0.05066 -0.0555 0.0097 1.0000
12.500 1.3760 0.05937 0.05568 -0.0534 0.0098 1.0000
12.750 1.3558 0.06445 0.06101 -0.0525 0.0098 1.0000
13.000 1.3096 0.07422 0.07123 -0.0536 0.0101 1.0000
13.250 1.2667 0.08487 0.08222 -0.0575 0.0105 1.0000
13.500 1.2335 0.09505 0.09263 -0.0630 0.0107 1.0000
13.750 1.2022 0.10631 0.10409 -0.0702 0.0109 1.0000
14.000 1.1698 0.11986 0.11779 -0.0794 0.0112 1.0000
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Polar data table (+)
Polar graphs
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