A18 (original) (a18-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 500,000 Max Cl/Cd: 99.59 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18-il-500000-n5.txt Download as CSV file: xf-a18-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5460 0.07996 0.07771 -0.0352 1.0000 0.0066
-10.500 -0.5748 0.07410 0.07189 -0.0360 1.0000 0.0064
-10.250 -0.5977 0.06624 0.06403 -0.0418 1.0000 0.0063
-10.000 -0.6029 0.02701 0.02373 -0.0913 0.9973 0.0060
-9.750 -0.5706 0.02329 0.01955 -0.0960 0.9961 0.0062
-9.500 -0.5380 0.02085 0.01674 -0.0991 0.9949 0.0064
-9.250 -0.5059 0.01856 0.01413 -0.1018 0.9933 0.0069
-9.000 -0.4734 0.01719 0.01255 -0.1037 0.9913 0.0073
-8.750 -0.4403 0.01610 0.01126 -0.1055 0.9895 0.0079
-8.500 -0.4071 0.01521 0.01020 -0.1071 0.9879 0.0086
-8.250 -0.3739 0.01443 0.00921 -0.1086 0.9867 0.0093
-8.000 -0.3419 0.01345 0.00802 -0.1098 0.9851 0.0105
-7.750 -0.3109 0.01270 0.00713 -0.1108 0.9826 0.0120
-7.500 -0.2785 0.01210 0.00641 -0.1119 0.9805 0.0138
-7.250 -0.2453 0.01152 0.00577 -0.1132 0.9787 0.0190
-7.000 -0.2122 0.01119 0.00548 -0.1144 0.9770 0.0285
-6.750 -0.1815 0.01098 0.00520 -0.1150 0.9733 0.0329
-6.500 -0.1503 0.01088 0.00509 -0.1156 0.9691 0.0369
-6.250 -0.1175 0.01076 0.00490 -0.1166 0.9657 0.0395
-6.000 -0.0878 0.01048 0.00457 -0.1170 0.9604 0.0420
-5.750 -0.0569 0.01028 0.00434 -0.1176 0.9556 0.0449
-5.500 -0.0257 0.01011 0.00413 -0.1183 0.9507 0.0475
-5.250 0.0038 0.00990 0.00387 -0.1185 0.9435 0.0495
-5.000 0.0346 0.00966 0.00355 -0.1191 0.9376 0.0508
-4.750 0.0636 0.00945 0.00328 -0.1192 0.9297 0.0516
-4.500 0.0935 0.00916 0.00293 -0.1196 0.9224 0.0533
-4.250 0.1225 0.00890 0.00263 -0.1197 0.9131 0.0559
-4.000 0.1514 0.00872 0.00241 -0.1198 0.9035 0.0585
-3.750 0.1800 0.00858 0.00222 -0.1199 0.8937 0.0612
-3.500 0.2084 0.00847 0.00206 -0.1198 0.8824 0.0641
-3.250 0.2366 0.00838 0.00190 -0.1198 0.8697 0.0671
-3.000 0.2648 0.00826 0.00177 -0.1197 0.8556 0.0741
-2.750 0.2928 0.00818 0.00166 -0.1196 0.8417 0.0836
-2.500 0.3210 0.00807 0.00158 -0.1197 0.8282 0.1056
-2.250 0.3491 0.00797 0.00153 -0.1197 0.8145 0.1345
-2.000 0.3772 0.00792 0.00149 -0.1197 0.8007 0.1561
-1.750 0.4052 0.00788 0.00146 -0.1197 0.7868 0.1789
-1.500 0.4332 0.00785 0.00146 -0.1197 0.7727 0.2057
-1.250 0.4608 0.00786 0.00146 -0.1196 0.7549 0.2333
-1.000 0.4883 0.00788 0.00146 -0.1195 0.7332 0.2559
-0.500 0.5429 0.00790 0.00158 -0.1193 0.6834 0.3671
-0.250 0.5702 0.00797 0.00163 -0.1192 0.6588 0.3988
0.000 0.5976 0.00799 0.00168 -0.1191 0.6361 0.4299
0.250 0.6248 0.00801 0.00177 -0.1191 0.6095 0.4831
0.500 0.6519 0.00796 0.00190 -0.1191 0.5854 0.5908
0.750 0.6782 0.00783 0.00204 -0.1189 0.5652 0.7204
1.000 0.6982 0.00738 0.00203 -0.1168 0.5510 1.0000
1.250 0.7257 0.00755 0.00215 -0.1168 0.5378 1.0000
1.500 0.7531 0.00774 0.00227 -0.1167 0.5219 1.0000
1.750 0.7803 0.00793 0.00240 -0.1166 0.5051 1.0000
2.000 0.8077 0.00811 0.00254 -0.1165 0.4798 1.0000
2.500 0.8585 0.00892 0.00294 -0.1159 0.3966 1.0000
2.750 0.8849 0.00921 0.00318 -0.1157 0.3722 1.0000
3.000 0.9060 0.01025 0.00359 -0.1149 0.2392 1.0000
3.500 0.9548 0.01139 0.00433 -0.1141 0.1580 1.0000
3.750 0.9801 0.01180 0.00465 -0.1138 0.1326 1.0000
4.000 1.0044 0.01235 0.00500 -0.1133 0.0931 1.0000
4.250 1.0274 0.01306 0.00549 -0.1127 0.0542 1.0000
4.500 1.0508 0.01371 0.00599 -0.1121 0.0266 1.0000
4.750 1.0745 0.01429 0.00651 -0.1115 0.0157 1.0000
5.000 1.0992 0.01472 0.00702 -0.1110 0.0131 1.0000
5.250 1.1235 0.01520 0.00756 -0.1104 0.0116 1.0000
5.500 1.1468 0.01579 0.00820 -0.1097 0.0102 1.0000
5.750 1.1688 0.01655 0.00905 -0.1087 0.0089 1.0000
6.000 1.1923 0.01706 0.00962 -0.1081 0.0083 1.0000
6.250 1.2148 0.01767 0.01030 -0.1073 0.0076 1.0000
6.500 1.2366 0.01835 0.01104 -0.1064 0.0071 1.0000
6.750 1.2578 0.01908 0.01186 -0.1054 0.0067 1.0000
7.000 1.2771 0.02000 0.01286 -0.1041 0.0063 1.0000
7.250 1.2934 0.02127 0.01423 -0.1023 0.0059 1.0000
7.500 1.3125 0.02215 0.01522 -0.1010 0.0057 1.0000
7.750 1.3311 0.02305 0.01623 -0.0996 0.0054 1.0000
8.000 1.3493 0.02396 0.01724 -0.0982 0.0051 1.0000
8.250 1.3669 0.02486 0.01824 -0.0968 0.0048 1.0000
8.500 1.3833 0.02586 0.01934 -0.0952 0.0046 1.0000
8.750 1.3983 0.02695 0.02053 -0.0934 0.0044 1.0000
9.000 1.4119 0.02810 0.02177 -0.0914 0.0043 1.0000
9.250 1.4231 0.02936 0.02317 -0.0891 0.0041 1.0000
9.500 1.4296 0.03094 0.02489 -0.0861 0.0040 1.0000
9.750 1.4307 0.03300 0.02714 -0.0824 0.0039 1.0000
10.000 1.4357 0.03462 0.02894 -0.0794 0.0038 1.0000
10.250 1.4392 0.03643 0.03096 -0.0764 0.0038 1.0000
10.500 1.4402 0.03854 0.03327 -0.0734 0.0037 1.0000
10.750 1.4391 0.04090 0.03586 -0.0705 0.0036 1.0000
11.000 1.4355 0.04358 0.03877 -0.0678 0.0036 1.0000
11.250 1.4294 0.04662 0.04206 -0.0654 0.0035 1.0000
11.500 1.4207 0.05010 0.04578 -0.0634 0.0035 1.0000
11.750 1.4097 0.05404 0.04996 -0.0619 0.0034 1.0000
12.000 1.3966 0.05853 0.05469 -0.0612 0.0034 1.0000
12.250 1.3812 0.06368 0.06007 -0.0613 0.0034 1.0000
12.500 1.3643 0.06941 0.06602 -0.0623 0.0034 1.0000
12.750 1.3457 0.07597 0.07280 -0.0643 0.0034 1.0000
13.000 1.3257 0.08328 0.08032 -0.0674 0.0034 1.0000
13.250 1.3050 0.09137 0.08860 -0.0713 0.0034 1.0000
13.500 1.2833 0.10043 0.09784 -0.0762 0.0034 1.0000
13.750 1.2614 0.11024 0.10781 -0.0818 0.0034 1.0000
14.000 1.2386 0.12107 0.11880 -0.0881 0.0035 1.0000
14.250 1.2157 0.13308 0.13095 -0.0950 0.0035 1.0000
14.500 1.1915 0.14585 0.14382 -0.1019 0.0036 1.0000
14.750 1.1651 0.15974 0.15779 -0.1092 0.0037 1.0000
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Polar data table (+)
Polar graphs
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