A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 100,000 Max Cl/Cd: 63.68 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18sm-il-100000-n5.txt Download as CSV file: xf-a18sm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4010 0.09618 0.09103 -0.0291 1.0000 0.0358
-8.000 -0.4054 0.09277 0.08770 -0.0294 1.0000 0.0341
-7.250 -0.4219 0.08018 0.07534 -0.0348 1.0000 0.0300
-7.000 -0.4192 0.07638 0.07159 -0.0366 1.0000 0.0298
-6.750 -0.4146 0.07212 0.06735 -0.0393 1.0000 0.0296
-6.500 -0.4069 0.06724 0.06248 -0.0432 1.0000 0.0295
-6.250 -0.3944 0.06139 0.05659 -0.0486 1.0000 0.0293
-6.000 -0.3742 0.05347 0.04852 -0.0569 1.0000 0.0293
-5.750 -0.3360 0.03912 0.03343 -0.0724 1.0000 0.0295
-5.500 -0.3025 0.03230 0.02579 -0.0791 1.0000 0.0318
-5.250 -0.2777 0.03039 0.02364 -0.0802 1.0000 0.0341
-5.000 -0.2475 0.02708 0.01972 -0.0824 1.0000 0.0360
-4.750 -0.2172 0.02448 0.01649 -0.0838 1.0000 0.0387
-4.500 -0.1894 0.02295 0.01462 -0.0845 1.0000 0.0430
-4.250 -0.1628 0.02194 0.01341 -0.0848 1.0000 0.0469
-4.000 -0.1342 0.02079 0.01191 -0.0852 1.0000 0.0517
-3.750 -0.0994 0.02000 0.01106 -0.0871 0.9974 0.0595
-3.500 -0.0610 0.01907 0.00994 -0.0894 0.9945 0.0679
-3.250 -0.0243 0.01850 0.00928 -0.0915 0.9900 0.0811
-3.000 0.0136 0.01797 0.00870 -0.0939 0.9858 0.0963
-2.750 0.0509 0.01756 0.00826 -0.0961 0.9811 0.1165
-2.500 0.0870 0.01718 0.00791 -0.0980 0.9754 0.1390
-2.250 0.1257 0.01685 0.00757 -0.1004 0.9711 0.1648
-2.000 0.1594 0.01657 0.00732 -0.1018 0.9640 0.1922
-1.750 0.1972 0.01626 0.00710 -0.1040 0.9588 0.2243
-1.500 0.2315 0.01600 0.00691 -0.1055 0.9518 0.2600
-1.250 0.2682 0.01571 0.00674 -0.1074 0.9459 0.3040
-1.000 0.3035 0.01544 0.00661 -0.1090 0.9392 0.3571
-0.750 0.3391 0.01512 0.00647 -0.1106 0.9325 0.4248
-0.500 0.3727 0.01471 0.00637 -0.1117 0.9252 0.5193
-0.250 0.3995 0.01375 0.00625 -0.1107 0.9179 0.7789
0.000 0.4303 0.01347 0.00599 -0.1109 0.9067 1.0000
0.250 0.4644 0.01343 0.00585 -0.1120 0.8981 1.0000
0.500 0.4978 0.01340 0.00572 -0.1129 0.8887 1.0000
0.750 0.5287 0.01340 0.00567 -0.1133 0.8773 1.0000
1.000 0.5602 0.01340 0.00562 -0.1138 0.8662 1.0000
1.250 0.5921 0.01339 0.00557 -0.1143 0.8550 1.0000
1.500 0.6238 0.01338 0.00553 -0.1148 0.8436 1.0000
1.750 0.6547 0.01339 0.00555 -0.1151 0.8312 1.0000
2.000 0.6844 0.01344 0.00559 -0.1151 0.8176 1.0000
2.250 0.7140 0.01350 0.00566 -0.1152 0.8036 1.0000
2.500 0.7433 0.01358 0.00575 -0.1151 0.7892 1.0000
2.750 0.7723 0.01367 0.00589 -0.1150 0.7743 1.0000
3.000 0.7995 0.01378 0.00601 -0.1144 0.7535 1.0000
3.250 0.8262 0.01385 0.00602 -0.1135 0.7255 1.0000
3.500 0.8522 0.01399 0.00610 -0.1125 0.6957 1.0000
3.750 0.8785 0.01419 0.00631 -0.1118 0.6715 1.0000
4.000 0.9044 0.01443 0.00655 -0.1110 0.6472 1.0000
4.250 0.9297 0.01470 0.00682 -0.1102 0.6207 1.0000
4.500 0.9545 0.01500 0.00711 -0.1092 0.5907 1.0000
4.750 0.9781 0.01536 0.00745 -0.1080 0.5533 1.0000
5.000 1.0001 0.01583 0.00777 -0.1065 0.5030 1.0000
5.250 1.0198 0.01648 0.00815 -0.1047 0.4294 1.0000
5.500 1.0358 0.01757 0.00868 -0.1026 0.3205 1.0000
5.750 1.0504 0.01906 0.00955 -0.1006 0.2218 1.0000
6.000 1.0674 0.02038 0.01055 -0.0991 0.1587 1.0000
6.250 1.0851 0.02164 0.01154 -0.0976 0.1111 1.0000
6.500 1.1026 0.02290 0.01263 -0.0961 0.0789 1.0000
6.750 1.1199 0.02417 0.01384 -0.0944 0.0614 1.0000
7.000 1.1371 0.02541 0.01510 -0.0927 0.0509 1.0000
7.250 1.1525 0.02685 0.01656 -0.0907 0.0450 1.0000
7.500 1.1699 0.02804 0.01794 -0.0890 0.0396 1.0000
7.750 1.1840 0.02963 0.01954 -0.0870 0.0356 1.0000
8.000 1.2005 0.03116 0.02124 -0.0851 0.0335 1.0000
8.250 1.2176 0.03284 0.02309 -0.0834 0.0315 1.0000
8.500 1.2352 0.03458 0.02498 -0.0818 0.0296 1.0000
8.750 1.2514 0.03625 0.02673 -0.0803 0.0275 1.0000
9.000 1.2672 0.03860 0.02922 -0.0789 0.0256 1.0000
9.250 1.2848 0.04076 0.03173 -0.0773 0.0245 1.0000
9.500 1.3005 0.04339 0.03470 -0.0756 0.0236 1.0000
9.750 1.3129 0.04625 0.03794 -0.0736 0.0228 1.0000
10.000 1.3211 0.04932 0.04139 -0.0712 0.0223 1.0000
10.250 1.3245 0.05250 0.04496 -0.0684 0.0218 1.0000
10.500 1.3239 0.05548 0.04827 -0.0654 0.0212 1.0000
10.750 1.3187 0.05813 0.05119 -0.0619 0.0207 1.0000
11.000 1.3108 0.06080 0.05410 -0.0586 0.0202 1.0000
11.250 1.3017 0.06368 0.05719 -0.0559 0.0197 1.0000
11.500 1.2907 0.06693 0.06065 -0.0537 0.0194 1.0000
11.750 1.2773 0.07068 0.06461 -0.0521 0.0191 1.0000
12.000 1.2615 0.07505 0.06920 -0.0513 0.0189 1.0000
12.250 1.2432 0.08009 0.07447 -0.0514 0.0188 1.0000
12.500 1.2231 0.08584 0.08046 -0.0527 0.0188 1.0000
12.750 1.1998 0.09279 0.08769 -0.0556 0.0190 1.0000
13.000 1.1592 0.10474 0.10004 -0.0629 0.0198 1.0000
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Polar data table (+)
Polar graphs
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