AG17 (ag17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.18 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag17-il-1000000-n5.txt Download as CSV file: xf-ag17-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG17
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5741 0.08738 0.08585 0.0102 1.0000 0.0030
-8.000 -0.5748 0.08234 0.08084 0.0068 1.0000 0.0029
-7.750 -0.5719 0.07638 0.07489 0.0008 1.0000 0.0029
-7.250 -0.5644 0.01963 0.01631 -0.0505 1.0000 0.0026
-7.000 -0.5398 0.01655 0.01274 -0.0511 1.0000 0.0027
-6.750 -0.5139 0.01489 0.01080 -0.0512 1.0000 0.0028
-6.500 -0.4875 0.01385 0.00957 -0.0512 1.0000 0.0029
-6.250 -0.4608 0.01310 0.00868 -0.0511 1.0000 0.0030
-6.000 -0.4345 0.01148 0.00678 -0.0512 1.0000 0.0035
-5.750 -0.4077 0.01093 0.00616 -0.0510 1.0000 0.0037
-5.500 -0.3809 0.01048 0.00565 -0.0509 1.0000 0.0040
-5.250 -0.3541 0.01001 0.00510 -0.0507 1.0000 0.0042
-5.000 -0.3274 0.00955 0.00456 -0.0504 1.0000 0.0045
-4.750 -0.2964 0.00908 0.00402 -0.0511 0.9965 0.0047
-4.500 -0.2635 0.00867 0.00355 -0.0522 0.9895 0.0051
-4.250 -0.2299 0.00838 0.00321 -0.0534 0.9800 0.0055
-4.000 -0.1969 0.00797 0.00272 -0.0544 0.9663 0.0060
-3.750 -0.1663 0.00758 0.00223 -0.0548 0.9467 0.0073
-3.500 -0.1390 0.00739 0.00196 -0.0545 0.9222 0.0087
-3.250 -0.1129 0.00726 0.00172 -0.0538 0.8945 0.0109
-3.000 -0.0865 0.00714 0.00152 -0.0533 0.8660 0.0158
-2.750 -0.0598 0.00704 0.00135 -0.0528 0.8374 0.0255
-2.500 -0.0328 0.00690 0.00118 -0.0525 0.8078 0.0467
-2.250 -0.0056 0.00680 0.00104 -0.0523 0.7784 0.0704
-2.000 0.0218 0.00670 0.00093 -0.0522 0.7499 0.1004
-1.750 0.0494 0.00658 0.00084 -0.0521 0.7222 0.1398
-1.500 0.0771 0.00650 0.00075 -0.0520 0.6949 0.1748
-1.250 0.1048 0.00642 0.00069 -0.0520 0.6672 0.2164
-1.000 0.1326 0.00638 0.00065 -0.0519 0.6396 0.2549
-0.750 0.1604 0.00636 0.00062 -0.0519 0.6121 0.2865
-0.500 0.1882 0.00634 0.00060 -0.0519 0.5837 0.3260
-0.250 0.2160 0.00633 0.00060 -0.0519 0.5553 0.3664
0.000 0.2438 0.00635 0.00061 -0.0518 0.5267 0.4032
0.250 0.2716 0.00636 0.00063 -0.0518 0.4984 0.4424
0.500 0.2994 0.00639 0.00066 -0.0518 0.4694 0.4847
0.750 0.3271 0.00640 0.00070 -0.0518 0.4414 0.5315
1.000 0.3547 0.00641 0.00076 -0.0518 0.4139 0.5853
1.250 0.3822 0.00639 0.00083 -0.0517 0.3876 0.6509
1.500 0.4092 0.00631 0.00091 -0.0515 0.3616 0.7355
1.750 0.4328 0.00585 0.00096 -0.0503 0.3375 1.0000
2.000 0.4606 0.00603 0.00104 -0.0502 0.3133 1.0000
2.250 0.4883 0.00622 0.00112 -0.0502 0.2889 1.0000
2.500 0.5160 0.00641 0.00121 -0.0501 0.2664 1.0000
2.750 0.5436 0.00662 0.00134 -0.0501 0.2429 1.0000
3.000 0.5712 0.00683 0.00145 -0.0500 0.2207 1.0000
3.250 0.5988 0.00704 0.00158 -0.0499 0.2011 1.0000
3.500 0.6263 0.00726 0.00172 -0.0499 0.1806 1.0000
3.750 0.6536 0.00750 0.00188 -0.0498 0.1613 1.0000
4.000 0.6810 0.00775 0.00206 -0.0497 0.1418 1.0000
4.250 0.7082 0.00800 0.00225 -0.0496 0.1243 1.0000
4.500 0.7354 0.00826 0.00245 -0.0495 0.1092 1.0000
4.750 0.7625 0.00855 0.00267 -0.0494 0.0917 1.0000
5.000 0.7894 0.00886 0.00293 -0.0492 0.0754 1.0000
5.250 0.8163 0.00916 0.00318 -0.0491 0.0627 1.0000
5.500 0.8432 0.00947 0.00345 -0.0490 0.0517 1.0000
5.750 0.8698 0.00981 0.00375 -0.0488 0.0405 1.0000
6.000 0.8963 0.01020 0.00409 -0.0486 0.0297 1.0000
6.250 0.9226 0.01059 0.00444 -0.0484 0.0213 1.0000
6.500 0.9488 0.01099 0.00483 -0.0482 0.0153 1.0000
6.750 0.9752 0.01134 0.00520 -0.0480 0.0121 1.0000
7.000 1.0012 0.01178 0.00564 -0.0477 0.0085 1.0000
7.250 1.0272 0.01218 0.00607 -0.0475 0.0068 1.0000
7.500 1.0527 0.01270 0.00661 -0.0472 0.0048 1.0000
7.750 1.0785 0.01314 0.00710 -0.0469 0.0040 1.0000
8.000 1.1037 0.01366 0.00765 -0.0466 0.0032 1.0000
8.250 1.1282 0.01437 0.00848 -0.0461 0.0026 1.0000
8.500 1.1532 0.01490 0.00908 -0.0458 0.0025 1.0000
8.750 1.1779 0.01548 0.00975 -0.0454 0.0023 1.0000
9.000 1.2021 0.01612 0.01047 -0.0450 0.0022 1.0000
9.250 1.2260 0.01680 0.01125 -0.0445 0.0021 1.0000
9.500 1.2494 0.01753 0.01208 -0.0440 0.0019 1.0000
9.750 1.2724 0.01829 0.01294 -0.0435 0.0018 1.0000
10.000 1.2950 0.01909 0.01384 -0.0429 0.0017 1.0000
10.250 1.3172 0.01992 0.01478 -0.0423 0.0016 1.0000
10.500 1.3385 0.02084 0.01583 -0.0417 0.0015 1.0000
10.750 1.3587 0.02194 0.01705 -0.0410 0.0014 1.0000
11.000 1.3759 0.02346 0.01876 -0.0399 0.0013 1.0000
11.250 1.3872 0.02580 0.02139 -0.0384 0.0011 1.0000
11.500 1.4039 0.02713 0.02286 -0.0375 0.0011 1.0000
11.750 1.4187 0.02858 0.02448 -0.0364 0.0011 1.0000
12.000 1.4312 0.03022 0.02629 -0.0352 0.0011 1.0000
12.250 1.4407 0.03206 0.02831 -0.0338 0.0010 1.0000
12.500 1.4464 0.03413 0.03057 -0.0322 0.0010 1.0000
12.750 1.4442 0.03641 0.03304 -0.0300 0.0010 1.0000
13.000 1.4364 0.03913 0.03594 -0.0282 0.0010 1.0000
13.250 1.4251 0.04291 0.03991 -0.0282 0.0010 1.0000
13.500 1.4115 0.04811 0.04531 -0.0307 0.0010 1.0000
13.750 1.3946 0.05524 0.05264 -0.0358 0.0010 1.0000
14.000 1.3727 0.06454 0.06214 -0.0427 0.0010 1.0000
14.250 1.3431 0.07588 0.07365 -0.0502 0.0010 1.0000
14.500 1.3080 0.08804 0.08596 -0.0571 0.0010 1.0000
14.750 1.2666 0.10110 0.09913 -0.0637 0.0011 1.0000
15.000 1.2286 0.11345 0.11157 -0.0696 0.0011 1.0000
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Polar data table (+)
Polar graphs
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