A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 500,000 Max Cl/Cd: 102.74 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18sm-il-500000-n5.txt Download as CSV file: xf-a18sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4281 0.09677 0.09439 -0.0283 1.0000 0.0090
-9.000 -0.4312 0.09251 0.09016 -0.0294 1.0000 0.0089
-8.750 -0.5702 0.03000 0.02697 -0.0861 0.9968 0.0081
-8.500 -0.5377 0.02433 0.02067 -0.0931 0.9955 0.0084
-8.250 -0.5055 0.02203 0.01806 -0.0962 0.9944 0.0087
-8.000 -0.4745 0.02038 0.01616 -0.0983 0.9929 0.0090
-7.750 -0.4433 0.01891 0.01444 -0.1001 0.9911 0.0094
-7.500 -0.4116 0.01757 0.01285 -0.1018 0.9894 0.0098
-7.250 -0.3792 0.01638 0.01143 -0.1035 0.9877 0.0102
-7.000 -0.3463 0.01534 0.01016 -0.1051 0.9862 0.0107
-6.750 -0.3129 0.01447 0.00910 -0.1067 0.9849 0.0111
-6.500 -0.2790 0.01356 0.00804 -0.1084 0.9838 0.0119
-6.250 -0.2477 0.01298 0.00738 -0.1095 0.9811 0.0130
-6.000 -0.2159 0.01246 0.00677 -0.1105 0.9783 0.0140
-5.750 -0.1828 0.01192 0.00611 -0.1118 0.9759 0.0152
-5.500 -0.1494 0.01143 0.00552 -0.1131 0.9738 0.0163
-5.250 -0.1158 0.01087 0.00491 -0.1145 0.9717 0.0186
-5.000 -0.0847 0.01053 0.00451 -0.1152 0.9680 0.0207
-4.750 -0.0542 0.01023 0.00414 -0.1158 0.9631 0.0230
-4.500 -0.0222 0.00986 0.00377 -0.1167 0.9594 0.0272
-4.250 0.0091 0.00962 0.00347 -0.1174 0.9551 0.0305
-4.000 0.0386 0.00931 0.00317 -0.1178 0.9490 0.0367
-3.750 0.0698 0.00908 0.00289 -0.1185 0.9440 0.0419
-3.500 0.0989 0.00885 0.00268 -0.1187 0.9370 0.0508
-3.250 0.1289 0.00863 0.00247 -0.1191 0.9304 0.0613
-3.000 0.1577 0.00846 0.00231 -0.1192 0.9221 0.0722
-2.750 0.1868 0.00829 0.00214 -0.1194 0.9139 0.0859
-2.500 0.2153 0.00815 0.00201 -0.1194 0.9040 0.0999
-2.250 0.2437 0.00802 0.00190 -0.1194 0.8935 0.1155
-2.000 0.2720 0.00792 0.00179 -0.1194 0.8824 0.1305
-1.750 0.3002 0.00783 0.00170 -0.1193 0.8703 0.1477
-1.500 0.3282 0.00775 0.00163 -0.1192 0.8575 0.1647
-1.250 0.3562 0.00768 0.00157 -0.1192 0.8436 0.1858
-1.000 0.3841 0.00763 0.00152 -0.1191 0.8293 0.2079
-0.750 0.4120 0.00759 0.00150 -0.1190 0.8144 0.2341
-0.500 0.4398 0.00755 0.00148 -0.1189 0.7991 0.2614
-0.250 0.4676 0.00752 0.00149 -0.1188 0.7834 0.2947
0.000 0.4954 0.00750 0.00150 -0.1187 0.7675 0.3285
0.250 0.5231 0.00749 0.00154 -0.1187 0.7514 0.3685
0.500 0.5508 0.00747 0.00158 -0.1186 0.7352 0.4119
0.750 0.5784 0.00744 0.00164 -0.1186 0.7192 0.4669
1.000 0.6059 0.00735 0.00172 -0.1185 0.7033 0.5491
1.250 0.6319 0.00700 0.00185 -0.1182 0.6855 0.7374
1.500 0.6529 0.00663 0.00180 -0.1162 0.6582 1.0000
1.750 0.6792 0.00688 0.00187 -0.1158 0.6229 1.0000
2.000 0.7057 0.00711 0.00196 -0.1155 0.5932 1.0000
2.250 0.7327 0.00732 0.00206 -0.1153 0.5710 1.0000
2.500 0.7599 0.00750 0.00219 -0.1151 0.5511 1.0000
2.750 0.7869 0.00771 0.00231 -0.1149 0.5308 1.0000
3.000 0.8137 0.00792 0.00245 -0.1147 0.5077 1.0000
3.250 0.8402 0.00818 0.00260 -0.1144 0.4804 1.0000
3.500 0.8659 0.00852 0.00280 -0.1140 0.4418 1.0000
3.750 0.8899 0.00909 0.00306 -0.1134 0.3739 1.0000
4.000 0.9125 0.00987 0.00342 -0.1127 0.2867 1.0000
4.250 0.9353 0.01067 0.00384 -0.1120 0.2121 1.0000
4.500 0.9593 0.01127 0.00422 -0.1114 0.1661 1.0000
4.750 0.9839 0.01176 0.00458 -0.1109 0.1337 1.0000
5.000 1.0081 0.01231 0.00496 -0.1104 0.0993 1.0000
5.250 1.0319 0.01289 0.00537 -0.1098 0.0685 1.0000
5.500 1.0559 0.01342 0.00578 -0.1092 0.0482 1.0000
5.750 1.0802 0.01390 0.00622 -0.1086 0.0363 1.0000
6.000 1.1047 0.01433 0.00665 -0.1081 0.0293 1.0000
6.250 1.1289 0.01478 0.00712 -0.1074 0.0241 1.0000
6.500 1.1526 0.01529 0.00761 -0.1068 0.0199 1.0000
6.750 1.1763 0.01577 0.00813 -0.1060 0.0174 1.0000
7.000 1.1999 0.01626 0.00868 -0.1053 0.0157 1.0000
7.250 1.2226 0.01682 0.00928 -0.1045 0.0142 1.0000
7.500 1.2437 0.01759 0.01010 -0.1033 0.0128 1.0000
7.750 1.2659 0.01817 0.01076 -0.1023 0.0123 1.0000
8.000 1.2876 0.01878 0.01145 -0.1013 0.0116 1.0000
8.250 1.3090 0.01939 0.01214 -0.1003 0.0108 1.0000
8.500 1.3299 0.02002 0.01282 -0.0992 0.0101 1.0000
8.750 1.3494 0.02079 0.01365 -0.0979 0.0095 1.0000
9.000 1.3654 0.02192 0.01487 -0.0960 0.0089 1.0000
9.250 1.3827 0.02286 0.01591 -0.0944 0.0087 1.0000
9.500 1.4000 0.02374 0.01691 -0.0927 0.0084 1.0000
9.750 1.4165 0.02466 0.01794 -0.0910 0.0081 1.0000
10.000 1.4324 0.02558 0.01899 -0.0892 0.0077 1.0000
10.250 1.4476 0.02648 0.01999 -0.0873 0.0073 1.0000
10.500 1.4621 0.02733 0.02092 -0.0854 0.0070 1.0000
10.750 1.4743 0.02824 0.02192 -0.0831 0.0067 1.0000
11.000 1.4832 0.02929 0.02308 -0.0803 0.0064 1.0000
11.250 1.4896 0.03061 0.02450 -0.0773 0.0062 1.0000
11.500 1.4917 0.03238 0.02641 -0.0739 0.0060 1.0000
11.750 1.4932 0.03430 0.02850 -0.0707 0.0059 1.0000
12.000 1.4985 0.03588 0.03024 -0.0682 0.0058 1.0000
12.250 1.5019 0.03769 0.03222 -0.0658 0.0056 1.0000
12.500 1.5035 0.03976 0.03450 -0.0634 0.0055 1.0000
12.750 1.5036 0.04202 0.03695 -0.0612 0.0054 1.0000
13.000 1.5018 0.04462 0.03974 -0.0592 0.0053 1.0000
13.250 1.4981 0.04751 0.04282 -0.0576 0.0052 1.0000
13.500 1.4928 0.05075 0.04627 -0.0563 0.0051 1.0000
13.750 1.4858 0.05438 0.05009 -0.0555 0.0050 1.0000
14.000 1.4768 0.05847 0.05439 -0.0552 0.0049 1.0000
14.250 1.4662 0.06305 0.05917 -0.0555 0.0049 1.0000
14.500 1.4526 0.06832 0.06464 -0.0564 0.0048 1.0000
14.750 1.4379 0.07412 0.07064 -0.0581 0.0048 1.0000
15.000 1.4215 0.08060 0.07731 -0.0605 0.0048 1.0000
15.250 1.4020 0.08805 0.08495 -0.0637 0.0047 1.0000
15.500 1.3807 0.09638 0.09348 -0.0678 0.0048 1.0000
15.750 1.3565 0.10588 0.10317 -0.0729 0.0048 1.0000
16.000 1.3301 0.11654 0.11402 -0.0789 0.0048 1.0000
16.250 1.3011 0.12875 0.12641 -0.0860 0.0049 1.0000
16.500 1.2659 0.14353 0.14138 -0.0946 0.0050 1.0000
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