AG18 (ag18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.13 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag18-il-1000000-n5.txt Download as CSV file: xf-ag18-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4546 0.11951 0.11796 0.0126 1.0000 0.0056
-9.500 -0.5684 0.11605 0.11443 0.0237 1.0000 0.0056
-8.000 -0.5568 0.08871 0.08717 0.0115 1.0000 0.0032
-7.750 -0.5509 0.08509 0.08357 0.0092 1.0000 0.0031
-7.500 -0.5439 0.08112 0.07960 0.0055 1.0000 0.0030
-7.250 -0.5340 0.07534 0.07383 -0.0012 1.0000 0.0029
-7.000 -0.5196 0.06880 0.06728 -0.0096 1.0000 0.0028
-6.750 -0.5000 0.06087 0.05932 -0.0200 1.0000 0.0028
-6.500 -0.4732 0.01848 0.01517 -0.0519 1.0000 0.0028
-6.250 -0.4472 0.01607 0.01236 -0.0523 1.0000 0.0029
-6.000 -0.4207 0.01491 0.01100 -0.0523 1.0000 0.0030
-5.750 -0.3944 0.01250 0.00816 -0.0526 1.0000 0.0034
-5.500 -0.3676 0.01181 0.00733 -0.0525 1.0000 0.0037
-5.250 -0.3408 0.01127 0.00671 -0.0523 1.0000 0.0039
-5.000 -0.3140 0.01069 0.00603 -0.0521 1.0000 0.0041
-4.750 -0.2873 0.01010 0.00535 -0.0519 1.0000 0.0043
-4.500 -0.2588 0.00950 0.00466 -0.0520 0.9986 0.0045
-4.250 -0.2254 0.00902 0.00411 -0.0532 0.9924 0.0049
-4.000 -0.1918 0.00863 0.00366 -0.0544 0.9829 0.0053
-3.750 -0.1583 0.00816 0.00309 -0.0556 0.9693 0.0055
-3.500 -0.1271 0.00776 0.00258 -0.0561 0.9479 0.0057
-3.250 -0.0998 0.00737 0.00202 -0.0557 0.9197 0.0064
-3.000 -0.0740 0.00718 0.00172 -0.0549 0.8889 0.0081
-2.750 -0.0477 0.00711 0.00151 -0.0543 0.8584 0.0097
-2.500 -0.0209 0.00700 0.00129 -0.0539 0.8279 0.0150
-2.250 0.0061 0.00692 0.00114 -0.0536 0.7978 0.0251
-2.000 0.0334 0.00683 0.00100 -0.0533 0.7688 0.0440
-1.750 0.0609 0.00673 0.00089 -0.0532 0.7411 0.0714
-1.500 0.0885 0.00664 0.00079 -0.0531 0.7138 0.1035
-1.250 0.1162 0.00655 0.00072 -0.0530 0.6863 0.1421
-1.000 0.1439 0.00647 0.00066 -0.0530 0.6583 0.1852
-0.750 0.1716 0.00639 0.00062 -0.0529 0.6287 0.2387
-0.500 0.1992 0.00634 0.00060 -0.0529 0.5975 0.2892
-0.250 0.2269 0.00633 0.00058 -0.0529 0.5651 0.3360
0.000 0.2546 0.00632 0.00059 -0.0529 0.5328 0.3872
0.250 0.2822 0.00634 0.00062 -0.0528 0.4989 0.4351
0.500 0.3098 0.00637 0.00065 -0.0528 0.4648 0.4851
0.750 0.3373 0.00638 0.00070 -0.0528 0.4326 0.5425
1.000 0.3647 0.00633 0.00076 -0.0527 0.4018 0.6235
1.250 0.3908 0.00606 0.00084 -0.0524 0.3728 0.7803
1.750 0.4430 0.00593 0.00095 -0.0513 0.3195 1.0000
2.000 0.4707 0.00612 0.00102 -0.0513 0.2938 1.0000
2.250 0.4983 0.00631 0.00111 -0.0512 0.2695 1.0000
2.500 0.5260 0.00650 0.00120 -0.0511 0.2474 1.0000
2.750 0.5535 0.00670 0.00131 -0.0511 0.2258 1.0000
3.000 0.5810 0.00691 0.00144 -0.0510 0.2051 1.0000
3.250 0.6085 0.00711 0.00157 -0.0509 0.1862 1.0000
3.500 0.6359 0.00735 0.00172 -0.0508 0.1652 1.0000
4.000 0.6905 0.00781 0.00205 -0.0506 0.1304 1.0000
4.250 0.7178 0.00804 0.00224 -0.0505 0.1157 1.0000
4.500 0.7449 0.00831 0.00244 -0.0504 0.1000 1.0000
4.750 0.7719 0.00860 0.00266 -0.0502 0.0851 1.0000
5.000 0.7989 0.00887 0.00289 -0.0501 0.0728 1.0000
5.250 0.8257 0.00917 0.00316 -0.0499 0.0607 1.0000
5.500 0.8526 0.00946 0.00342 -0.0498 0.0510 1.0000
5.750 0.8793 0.00977 0.00371 -0.0496 0.0417 1.0000
6.000 0.9058 0.01012 0.00403 -0.0494 0.0328 1.0000
6.250 0.9321 0.01051 0.00438 -0.0492 0.0240 1.0000
6.500 0.9583 0.01092 0.00476 -0.0490 0.0175 1.0000
6.750 0.9846 0.01127 0.00515 -0.0488 0.0138 1.0000
7.000 1.0105 0.01172 0.00559 -0.0485 0.0099 1.0000
7.250 1.0365 0.01211 0.00602 -0.0483 0.0077 1.0000
7.500 1.0619 0.01265 0.00656 -0.0480 0.0052 1.0000
7.750 1.0876 0.01308 0.00704 -0.0477 0.0043 1.0000
8.000 1.1128 0.01360 0.00760 -0.0474 0.0034 1.0000
8.250 1.1375 0.01429 0.00837 -0.0469 0.0027 1.0000
8.500 1.1625 0.01481 0.00899 -0.0466 0.0025 1.0000
8.750 1.1871 0.01539 0.00966 -0.0462 0.0024 1.0000
9.000 1.2115 0.01601 0.01038 -0.0458 0.0022 1.0000
9.250 1.2354 0.01668 0.01114 -0.0453 0.0020 1.0000
9.500 1.2590 0.01739 0.01194 -0.0449 0.0018 1.0000
9.750 1.2821 0.01815 0.01280 -0.0444 0.0017 1.0000
10.000 1.3044 0.01904 0.01379 -0.0438 0.0015 1.0000
10.250 1.3244 0.02036 0.01528 -0.0430 0.0013 1.0000
10.500 1.3423 0.02200 0.01715 -0.0420 0.0012 1.0000
10.750 1.3623 0.02309 0.01841 -0.0412 0.0012 1.0000
11.000 1.3811 0.02433 0.01980 -0.0404 0.0011 1.0000
11.250 1.3983 0.02574 0.02139 -0.0394 0.0011 1.0000
11.500 1.4135 0.02734 0.02318 -0.0383 0.0011 1.0000
11.750 1.4264 0.02914 0.02519 -0.0371 0.0010 1.0000
12.000 1.4363 0.03119 0.02745 -0.0357 0.0010 1.0000
12.250 1.4424 0.03348 0.02997 -0.0342 0.0010 1.0000
12.500 1.4437 0.03602 0.03274 -0.0325 0.0010 1.0000
12.750 1.4358 0.03871 0.03563 -0.0300 0.0010 1.0000
13.000 1.4235 0.04217 0.03928 -0.0291 0.0010 1.0000
13.250 1.4085 0.04713 0.04444 -0.0309 0.0010 1.0000
13.500 1.3910 0.05415 0.05167 -0.0359 0.0010 1.0000
13.750 1.3695 0.06377 0.06150 -0.0436 0.0010 1.0000
14.000 1.3406 0.07567 0.07357 -0.0518 0.0010 1.0000
14.250 1.3068 0.08784 0.08587 -0.0587 0.0010 1.0000
14.500 1.2708 0.09985 0.09797 -0.0647 0.0010 1.0000
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Polar data table (+)
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