A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 200,000 Max Cl/Cd: 87 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18sm-il-200000.txt Download as CSV file: xf-a18sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3979 0.09146 0.08795 -0.0275 1.0000 0.0488
-7.500 -0.4073 0.08940 0.08597 -0.0265 1.0000 0.0501
-7.250 -0.4148 0.08670 0.08336 -0.0308 1.0000 0.0519
-7.000 -0.4124 0.08293 0.07962 -0.0377 1.0000 0.0525
-6.750 -0.4046 0.07861 0.07530 -0.0425 1.0000 0.0527
-6.500 -0.4093 0.07367 0.07043 -0.0398 1.0000 0.0537
-6.250 -0.4054 0.07164 0.06842 -0.0366 1.0000 0.0547
-6.000 -0.3993 0.07008 0.06688 -0.0343 1.0000 0.0569
-5.750 -0.3886 0.06703 0.06383 -0.0364 1.0000 0.0604
-5.500 -0.3513 0.05618 0.05272 -0.0554 1.0000 0.0664
-5.250 -0.3421 0.05417 0.05075 -0.0534 1.0000 0.0675
-5.000 -0.2911 0.03844 0.03427 -0.0700 1.0000 0.0545
-4.750 -0.2785 0.03922 0.03523 -0.0673 1.0000 0.0576
-4.500 -0.1963 0.02086 0.01426 -0.0835 1.0000 0.0423
-4.250 -0.1698 0.02006 0.01339 -0.0839 1.0000 0.0468
-4.000 -0.1391 0.01877 0.01174 -0.0846 1.0000 0.0506
-3.750 -0.1086 0.01755 0.01031 -0.0855 1.0000 0.0562
-3.500 -0.0816 0.01709 0.00974 -0.0856 1.0000 0.0628
-3.250 -0.0410 0.01621 0.00877 -0.0883 0.9975 0.0729
-3.000 0.0005 0.01560 0.00812 -0.0913 0.9950 0.0870
-2.750 0.0406 0.01517 0.00763 -0.0939 0.9912 0.1064
-2.500 0.0811 0.01473 0.00728 -0.0968 0.9873 0.1305
-2.250 0.1233 0.01442 0.00702 -0.1000 0.9842 0.1595
-2.000 0.1612 0.01412 0.00679 -0.1023 0.9785 0.1891
-1.750 0.2016 0.01379 0.00658 -0.1051 0.9740 0.2229
-1.500 0.2446 0.01346 0.00639 -0.1084 0.9707 0.2657
-1.250 0.2795 0.01313 0.00626 -0.1100 0.9631 0.3143
-1.000 0.3212 0.01271 0.00610 -0.1131 0.9590 0.3851
-0.750 0.3591 0.01223 0.00598 -0.1152 0.9533 0.4824
-0.500 0.3931 0.01122 0.00589 -0.1163 0.9482 0.7446
-0.250 0.4331 0.01063 0.00548 -0.1181 0.9438 1.0000
0.000 0.4666 0.01052 0.00528 -0.1191 0.9344 1.0000
0.250 0.5069 0.01030 0.00499 -0.1213 0.9295 1.0000
0.500 0.5381 0.01019 0.00483 -0.1217 0.9188 1.0000
0.750 0.5703 0.01006 0.00467 -0.1222 0.9088 1.0000
1.000 0.6034 0.00990 0.00447 -0.1228 0.8995 1.0000
1.250 0.6338 0.00979 0.00433 -0.1229 0.8880 1.0000
1.500 0.6625 0.00974 0.00427 -0.1226 0.8746 1.0000
1.750 0.6908 0.00971 0.00421 -0.1222 0.8606 1.0000
2.000 0.7188 0.00971 0.00418 -0.1218 0.8458 1.0000
2.250 0.7452 0.00971 0.00415 -0.1209 0.8258 1.0000
2.500 0.7715 0.00970 0.00406 -0.1198 0.8025 1.0000
2.750 0.7970 0.00978 0.00408 -0.1188 0.7774 1.0000
3.000 0.8235 0.00992 0.00417 -0.1181 0.7565 1.0000
3.250 0.8498 0.01008 0.00429 -0.1175 0.7355 1.0000
3.500 0.8760 0.01027 0.00446 -0.1168 0.7143 1.0000
3.750 0.9018 0.01047 0.00462 -0.1161 0.6913 1.0000
4.000 0.9272 0.01069 0.00481 -0.1152 0.6658 1.0000
4.250 0.9518 0.01094 0.00498 -0.1142 0.6356 1.0000
4.500 0.9758 0.01123 0.00520 -0.1131 0.6002 1.0000
4.750 0.9992 0.01158 0.00544 -0.1120 0.5607 1.0000
5.000 1.0218 0.01199 0.00572 -0.1107 0.5120 1.0000
5.250 1.0423 0.01258 0.00605 -0.1092 0.4438 1.0000
5.500 1.0583 0.01367 0.00656 -0.1071 0.3255 1.0000
5.750 1.0720 0.01527 0.00748 -0.1050 0.2079 1.0000
6.000 1.0874 0.01683 0.00849 -0.1033 0.1229 1.0000
6.250 1.1029 0.01845 0.00972 -0.1012 0.0726 1.0000
6.500 1.1202 0.01978 0.01099 -0.0994 0.0562 1.0000
6.750 1.1381 0.02102 0.01224 -0.0976 0.0480 1.0000
7.000 1.1550 0.02250 0.01379 -0.0955 0.0436 1.0000
7.250 1.1742 0.02369 0.01507 -0.0939 0.0396 1.0000
7.500 1.1902 0.02588 0.01722 -0.0921 0.0356 1.0000
7.750 1.2119 0.02730 0.01879 -0.0908 0.0340 1.0000
8.000 1.2342 0.02901 0.02067 -0.0896 0.0325 1.0000
8.250 1.2567 0.03103 0.02289 -0.0885 0.0313 1.0000
8.500 1.2783 0.03319 0.02526 -0.0873 0.0301 1.0000
8.750 1.2972 0.03493 0.02716 -0.0861 0.0283 1.0000
9.000 1.3149 0.03804 0.03042 -0.0849 0.0268 1.0000
9.250 1.3292 0.04215 0.03492 -0.0830 0.0265 1.0000
9.500 1.3394 0.04599 0.03916 -0.0806 0.0264 1.0000
9.750 1.3475 0.04922 0.04277 -0.0778 0.0266 1.0000
10.000 1.3524 0.05214 0.04614 -0.0744 0.0273 1.0000
10.250 1.3163 0.06149 0.05662 -0.0665 0.0321 1.0000
10.500 1.3004 0.06656 0.06196 -0.0626 0.0335 1.0000
10.750 1.1898 0.05940 0.05509 -0.0452 0.0317 1.0000
11.000 1.1626 0.06397 0.05987 -0.0418 0.0322 1.0000
11.250 1.1345 0.06886 0.06495 -0.0396 0.0325 1.0000
11.500 1.1056 0.07415 0.07041 -0.0384 0.0328 1.0000
11.750 1.0759 0.07986 0.07629 -0.0385 0.0329 1.0000
12.000 1.0451 0.08606 0.08265 -0.0397 0.0330 1.0000
12.250 1.0131 0.09283 0.08956 -0.0421 0.0330 1.0000
12.500 0.9794 0.10026 0.09710 -0.0457 0.0331 1.0000
12.750 0.9429 0.10831 0.10525 -0.0503 0.0333 1.0000
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Polar data table (+)
Polar graphs
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