AG18 (ag18-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 50,000 Max Cl/Cd: 35.54 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag18-il-50000.txt Download as CSV file: xf-ag18-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG18
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5308 0.10601 0.09952 0.0127 1.0000 0.1847
-7.500 -0.5193 0.10145 0.09498 0.0132 1.0000 0.1917
-7.250 -0.5280 0.10046 0.09413 0.0066 1.0000 0.1997
-7.000 -0.5135 0.09563 0.08932 0.0092 1.0000 0.2119
-6.750 -0.5042 0.09186 0.08560 0.0089 1.0000 0.2247
-6.500 -0.4976 0.08866 0.08247 0.0065 1.0000 0.2394
-6.250 -0.4907 0.08544 0.07931 0.0031 1.0000 0.2550
-6.000 -0.4770 0.08115 0.07506 0.0064 1.0000 0.2721
-5.750 -0.4662 0.07779 0.07168 0.0060 1.0000 0.2920
-5.000 -0.4318 0.06744 0.06148 0.0061 1.0000 0.3595
-4.750 -0.4217 0.06443 0.05854 0.0057 1.0000 0.3931
-4.500 -0.4094 0.06095 0.05512 0.0086 1.0000 0.4224
-4.250 -0.2848 0.04015 0.03229 -0.0470 1.0000 0.1262
-4.000 -0.2501 0.03501 0.02638 -0.0499 1.0000 0.1137
-3.750 -0.2188 0.03144 0.02216 -0.0512 1.0000 0.1154
-3.500 -0.1892 0.02838 0.01864 -0.0516 1.0000 0.1208
-3.250 -0.1595 0.02569 0.01553 -0.0515 1.0000 0.1255
-3.000 -0.1307 0.02351 0.01302 -0.0511 1.0000 0.1413
-2.750 -0.1030 0.02151 0.01091 -0.0505 1.0000 0.1679
-2.500 -0.0759 0.01970 0.00914 -0.0496 1.0000 0.2270
-2.250 -0.0490 0.01744 0.00778 -0.0487 1.0000 0.3851
-2.000 -0.0401 0.01468 0.00696 -0.0426 1.0000 0.7292
-1.750 -0.0065 0.01389 0.00576 -0.0428 1.0000 1.0000
-1.500 0.0209 0.01390 0.00525 -0.0429 1.0000 1.0000
-1.250 0.0473 0.01393 0.00489 -0.0428 1.0000 1.0000
-1.000 0.0732 0.01398 0.00458 -0.0426 1.0000 1.0000
-0.750 0.0988 0.01406 0.00440 -0.0424 1.0000 1.0000
-0.500 0.1240 0.01416 0.00430 -0.0422 1.0000 1.0000
-0.250 0.1489 0.01428 0.00426 -0.0420 1.0000 1.0000
0.000 0.1736 0.01444 0.00426 -0.0418 1.0000 1.0000
0.250 0.1979 0.01463 0.00435 -0.0416 1.0000 1.0000
0.500 0.2220 0.01487 0.00451 -0.0415 1.0000 1.0000
0.750 0.2460 0.01515 0.00475 -0.0415 1.0000 1.0000
1.000 0.2696 0.01549 0.00507 -0.0416 1.0000 1.0000
1.250 0.2927 0.01591 0.00548 -0.0418 1.0000 1.0000
1.500 0.3152 0.01641 0.00600 -0.0421 1.0000 1.0000
1.750 0.3369 0.01702 0.00665 -0.0426 1.0000 1.0000
2.000 0.3577 0.01778 0.00747 -0.0434 1.0000 1.0000
2.250 0.3797 0.01872 0.00851 -0.0449 0.9985 1.0000
2.500 0.4743 0.01946 0.00958 -0.0586 0.9538 1.0000
2.750 0.5537 0.01949 0.00998 -0.0673 0.9049 1.0000
3.000 0.6056 0.01925 0.01007 -0.0691 0.8551 1.0000
3.250 0.6379 0.01910 0.01002 -0.0667 0.8047 1.0000
3.500 0.6605 0.01918 0.01009 -0.0628 0.7515 1.0000
3.750 0.6811 0.01940 0.01023 -0.0588 0.6968 1.0000
4.000 0.7017 0.01978 0.01047 -0.0553 0.6409 1.0000
4.250 0.7229 0.02034 0.01092 -0.0522 0.5838 1.0000
4.500 0.7447 0.02107 0.01147 -0.0497 0.5274 1.0000
4.750 0.7670 0.02196 0.01215 -0.0476 0.4734 1.0000
5.000 0.7894 0.02301 0.01299 -0.0457 0.4221 1.0000
5.250 0.8122 0.02425 0.01412 -0.0442 0.3733 1.0000
5.500 0.8352 0.02561 0.01544 -0.0428 0.3294 1.0000
5.750 0.8585 0.02720 0.01699 -0.0415 0.2902 1.0000
6.000 0.8814 0.02880 0.01852 -0.0403 0.2542 1.0000
6.250 0.9049 0.03087 0.02073 -0.0393 0.2244 1.0000
6.500 0.9272 0.03287 0.02283 -0.0382 0.1959 1.0000
6.750 0.9503 0.03549 0.02551 -0.0371 0.1749 1.0000
7.000 0.9708 0.03797 0.02834 -0.0360 0.1529 1.0000
7.250 0.9904 0.04203 0.03297 -0.0350 0.1412 1.0000
7.500 1.0088 0.04482 0.03602 -0.0340 0.1251 1.0000
7.750 1.0212 0.04993 0.04181 -0.0332 0.1186 1.0000
8.000 1.0284 0.05593 0.04850 -0.0329 0.1164 1.0000
8.250 1.0297 0.06238 0.05552 -0.0332 0.1159 1.0000
8.500 1.0243 0.06926 0.06283 -0.0345 0.1167 1.0000
8.750 1.0151 0.07628 0.07012 -0.0364 0.1187 1.0000
9.000 1.0056 0.08302 0.07700 -0.0386 0.1205 1.0000
9.250 0.9978 0.08949 0.08354 -0.0408 0.1217 1.0000
9.500 0.9914 0.09572 0.08982 -0.0426 0.1230 1.0000
9.750 0.9007 0.12924 0.12287 -0.0850 0.2979 1.0000
10.000 0.8997 0.13326 0.12688 -0.0851 0.2840 1.0000
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Polar data table (+)
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