A18 (original) (a18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (original) (a18-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.73 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18-il-1000000.txt Download as CSV file: xf-a18-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4536 0.09979 0.09812 -0.0263 1.0000 0.0103
-10.500 -0.6783 0.02377 0.02089 -0.0897 1.0000 0.0080
-10.250 -0.6539 0.01960 0.01623 -0.0929 0.9998 0.0084
-10.000 -0.6217 0.01792 0.01433 -0.0952 0.9991 0.0088
-9.750 -0.5896 0.01672 0.01295 -0.0969 0.9982 0.0092
-9.500 -0.5573 0.01567 0.01175 -0.0985 0.9974 0.0097
-9.250 -0.5241 0.01471 0.01062 -0.1001 0.9965 0.0102
-9.000 -0.4900 0.01390 0.00966 -0.1018 0.9956 0.0107
-8.750 -0.4554 0.01323 0.00886 -0.1035 0.9948 0.0111
-8.500 -0.4215 0.01193 0.00733 -0.1054 0.9943 0.0125
-8.250 -0.3900 0.01142 0.00676 -0.1063 0.9928 0.0137
-8.000 -0.3576 0.01097 0.00621 -0.1073 0.9913 0.0147
-7.750 -0.3245 0.01029 0.00543 -0.1086 0.9899 0.0168
-7.500 -0.2910 0.00988 0.00499 -0.1098 0.9885 0.0195
-7.250 -0.2574 0.00948 0.00459 -0.1111 0.9874 0.0244
-7.000 -0.2236 0.00926 0.00439 -0.1124 0.9863 0.0296
-6.750 -0.1892 0.00925 0.00442 -0.1137 0.9853 0.0337
-6.500 -0.1544 0.00929 0.00444 -0.1151 0.9844 0.0353
-6.250 -0.1194 0.00882 0.00394 -0.1168 0.9836 0.0392
-6.000 -0.0891 0.00872 0.00385 -0.1172 0.9798 0.0416
-5.750 -0.0572 0.00860 0.00371 -0.1180 0.9761 0.0438
-5.500 -0.0251 0.00848 0.00356 -0.1187 0.9728 0.0451
-5.250 0.0066 0.00817 0.00320 -0.1196 0.9699 0.0475
-5.000 0.0346 0.00789 0.00292 -0.1195 0.9637 0.0510
-4.750 0.0642 0.00769 0.00270 -0.1197 0.9587 0.0529
-4.500 0.0928 0.00753 0.00251 -0.1197 0.9523 0.0549
-4.250 0.1212 0.00738 0.00232 -0.1197 0.9452 0.0566
-4.000 0.1494 0.00727 0.00217 -0.1196 0.9374 0.0577
-3.750 0.1777 0.00703 0.00187 -0.1195 0.9292 0.0616
-3.500 0.2059 0.00687 0.00172 -0.1194 0.9194 0.0660
-3.250 0.2339 0.00678 0.00159 -0.1193 0.9095 0.0695
-3.000 0.2620 0.00667 0.00145 -0.1192 0.8985 0.0763
-2.500 0.3181 0.00639 0.00128 -0.1191 0.8726 0.1303
-2.250 0.3461 0.00631 0.00123 -0.1191 0.8582 0.1587
-2.000 0.3741 0.00625 0.00120 -0.1190 0.8419 0.1858
-1.750 0.4019 0.00623 0.00119 -0.1189 0.8220 0.2154
-1.500 0.4295 0.00624 0.00117 -0.1188 0.8017 0.2390
-1.250 0.4575 0.00623 0.00116 -0.1187 0.7830 0.2640
-1.000 0.4855 0.00616 0.00119 -0.1188 0.7633 0.3216
-0.750 0.5132 0.00619 0.00124 -0.1187 0.7433 0.3704
-0.500 0.5411 0.00623 0.00127 -0.1187 0.7252 0.3931
-0.250 0.5690 0.00627 0.00130 -0.1187 0.7045 0.4172
0.000 0.5969 0.00618 0.00137 -0.1188 0.6824 0.5028
0.250 0.6244 0.00590 0.00151 -0.1190 0.6572 0.6988
0.500 0.6449 0.00533 0.00149 -0.1171 0.6328 1.0000
0.750 0.6724 0.00551 0.00156 -0.1171 0.6073 1.0000
1.000 0.7000 0.00569 0.00163 -0.1170 0.5851 1.0000
1.250 0.7275 0.00587 0.00172 -0.1170 0.5642 1.0000
1.500 0.7549 0.00608 0.00184 -0.1169 0.5424 1.0000
1.750 0.7823 0.00628 0.00195 -0.1168 0.5213 1.0000
2.000 0.8095 0.00649 0.00206 -0.1168 0.4958 1.0000
2.250 0.8355 0.00688 0.00219 -0.1165 0.4311 1.0000
2.500 0.8613 0.00730 0.00242 -0.1162 0.3964 1.0000
2.750 0.8883 0.00753 0.00259 -0.1162 0.3711 1.0000
3.000 0.9104 0.00850 0.00296 -0.1155 0.2430 1.0000
3.250 0.9352 0.00907 0.00330 -0.1151 0.1933 1.0000
3.500 0.9612 0.00944 0.00355 -0.1149 0.1679 1.0000
3.750 0.9874 0.00976 0.00378 -0.1147 0.1462 1.0000
4.000 1.0130 0.01015 0.00404 -0.1145 0.1175 1.0000
4.250 1.0361 0.01091 0.00449 -0.1139 0.0630 1.0000
4.500 1.0591 0.01167 0.00502 -0.1132 0.0254 1.0000
4.750 1.0839 0.01217 0.00547 -0.1127 0.0179 1.0000
5.000 1.1086 0.01266 0.00600 -0.1121 0.0152 1.0000
5.250 1.1338 0.01305 0.00643 -0.1117 0.0141 1.0000
5.500 1.1585 0.01348 0.00690 -0.1112 0.0129 1.0000
5.750 1.1819 0.01409 0.00755 -0.1105 0.0116 1.0000
6.000 1.2036 0.01493 0.00849 -0.1095 0.0108 1.0000
6.250 1.2275 0.01541 0.00901 -0.1089 0.0104 1.0000
6.500 1.2505 0.01598 0.00964 -0.1081 0.0099 1.0000
6.750 1.2729 0.01661 0.01032 -0.1073 0.0094 1.0000
7.000 1.2949 0.01726 0.01104 -0.1064 0.0090 1.0000
7.250 1.3162 0.01796 0.01178 -0.1054 0.0085 1.0000
7.500 1.3356 0.01888 0.01275 -0.1041 0.0081 1.0000
7.750 1.3466 0.02091 0.01494 -0.1014 0.0075 1.0000
8.000 1.3689 0.02136 0.01545 -0.1006 0.0073 1.0000
8.250 1.3883 0.02220 0.01637 -0.0993 0.0071 1.0000
8.500 1.4063 0.02318 0.01747 -0.0979 0.0068 1.0000
8.750 1.4231 0.02429 0.01868 -0.0962 0.0066 1.0000
9.000 1.4391 0.02545 0.01994 -0.0945 0.0064 1.0000
9.250 1.4540 0.02667 0.02128 -0.0927 0.0063 1.0000
9.500 1.4682 0.02785 0.02257 -0.0908 0.0061 1.0000
9.750 1.4803 0.02914 0.02399 -0.0886 0.0060 1.0000
10.000 1.4906 0.03039 0.02535 -0.0861 0.0058 1.0000
10.250 1.4978 0.03164 0.02671 -0.0832 0.0057 1.0000
10.500 1.5019 0.03302 0.02822 -0.0799 0.0056 1.0000
10.750 1.5052 0.03450 0.02981 -0.0768 0.0055 1.0000
11.000 1.5050 0.03646 0.03190 -0.0735 0.0054 1.0000
11.250 1.5004 0.03899 0.03461 -0.0701 0.0053 1.0000
11.500 1.4891 0.04239 0.03824 -0.0665 0.0052 1.0000
11.750 1.4660 0.04735 0.04351 -0.0628 0.0051 1.0000
12.000 1.4465 0.05202 0.04844 -0.0604 0.0051 1.0000
12.250 1.4206 0.05787 0.05457 -0.0590 0.0051 1.0000
12.750 1.3872 0.06835 0.06544 -0.0600 0.0050 1.0000
13.000 1.3718 0.07411 0.07137 -0.0618 0.0050 1.0000
13.250 1.3446 0.08239 0.07986 -0.0649 0.0050 1.0000
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Polar data table (+)
Polar graphs
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