AG17 (ag17-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 500,000 Max Cl/Cd: 82.11 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag17-il-500000.txt Download as CSV file: xf-ag17-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5594 0.10773 0.10552 0.0179 1.0000 0.0134
-8.750 -0.5552 0.10382 0.10163 0.0159 1.0000 0.0138
-8.500 -0.5511 0.09983 0.09763 0.0137 1.0000 0.0143
-8.250 -0.5468 0.09575 0.09358 0.0110 1.0000 0.0148
-8.000 -0.5410 0.09169 0.08954 0.0079 1.0000 0.0154
-7.750 -0.5337 0.08796 0.08583 0.0049 1.0000 0.0157
-7.500 -0.5271 0.08385 0.08174 0.0013 1.0000 0.0159
-7.250 -0.5161 0.07890 0.07681 -0.0043 1.0000 0.0159
-7.000 -0.5020 0.07332 0.07123 -0.0111 1.0000 0.0160
-6.750 -0.4846 0.06692 0.06481 -0.0191 1.0000 0.0160
-6.500 -0.4634 0.05938 0.05719 -0.0280 1.0000 0.0161
-6.250 -0.4418 0.05137 0.04901 -0.0357 1.0000 0.0161
-6.000 -0.4309 0.03848 0.03570 -0.0452 1.0000 0.0173
-5.750 -0.4095 0.03481 0.03185 -0.0472 1.0000 0.0180
-5.500 -0.3862 0.03154 0.02837 -0.0487 1.0000 0.0188
-5.250 -0.3615 0.02798 0.02450 -0.0499 1.0000 0.0199
-5.000 -0.3314 0.01740 0.01257 -0.0506 1.0000 0.0119
-4.750 -0.3048 0.01551 0.01038 -0.0504 1.0000 0.0124
-4.500 -0.2783 0.01410 0.00876 -0.0500 1.0000 0.0130
-4.250 -0.2522 0.01346 0.00802 -0.0496 1.0000 0.0146
-4.000 -0.2258 0.01218 0.00657 -0.0491 1.0000 0.0150
-3.750 -0.1993 0.01104 0.00526 -0.0486 1.0000 0.0153
-3.500 -0.1729 0.01033 0.00446 -0.0481 1.0000 0.0161
-3.250 -0.1454 0.00907 0.00307 -0.0480 1.0000 0.0207
-3.000 -0.1185 0.00855 0.00252 -0.0477 1.0000 0.0311
-2.750 -0.0915 0.00799 0.00213 -0.0476 1.0000 0.0740
-2.500 -0.0648 0.00758 0.00195 -0.0476 1.0000 0.1322
-2.250 -0.0354 0.00720 0.00181 -0.0482 0.9989 0.2038
-2.000 0.0043 0.00681 0.00170 -0.0509 0.9938 0.2917
-1.750 0.0425 0.00649 0.00161 -0.0532 0.9862 0.3653
-1.500 0.0796 0.00621 0.00152 -0.0552 0.9765 0.4356
-1.250 0.1149 0.00594 0.00145 -0.0567 0.9634 0.5046
-1.000 0.1470 0.00567 0.00139 -0.0574 0.9456 0.5807
-0.750 0.1744 0.00535 0.00135 -0.0570 0.9231 0.6763
-0.500 0.1956 0.00488 0.00131 -0.0549 0.8972 0.8233
-0.250 0.2229 0.00463 0.00121 -0.0540 0.8698 1.0000
0.000 0.2490 0.00474 0.00115 -0.0533 0.8404 1.0000
0.250 0.2753 0.00486 0.00112 -0.0526 0.8101 1.0000
0.500 0.3018 0.00500 0.00110 -0.0520 0.7790 1.0000
0.750 0.3285 0.00516 0.00109 -0.0516 0.7479 1.0000
1.000 0.3555 0.00531 0.00110 -0.0512 0.7161 1.0000
1.250 0.3825 0.00549 0.00112 -0.0508 0.6835 1.0000
1.500 0.4096 0.00567 0.00116 -0.0505 0.6501 1.0000
1.750 0.4367 0.00587 0.00121 -0.0502 0.6154 1.0000
2.000 0.4638 0.00608 0.00128 -0.0500 0.5802 1.0000
2.250 0.4909 0.00631 0.00135 -0.0497 0.5437 1.0000
2.500 0.5180 0.00654 0.00145 -0.0495 0.5064 1.0000
2.750 0.5451 0.00680 0.00158 -0.0493 0.4695 1.0000
3.000 0.5721 0.00708 0.00171 -0.0492 0.4324 1.0000
3.250 0.5991 0.00735 0.00185 -0.0490 0.3955 1.0000
3.500 0.6261 0.00765 0.00202 -0.0489 0.3597 1.0000
3.750 0.6531 0.00796 0.00220 -0.0487 0.3263 1.0000
4.000 0.6799 0.00828 0.00243 -0.0486 0.2928 1.0000
4.250 0.7068 0.00861 0.00265 -0.0484 0.2619 1.0000
4.500 0.7335 0.00897 0.00289 -0.0483 0.2306 1.0000
4.750 0.7602 0.00933 0.00316 -0.0481 0.2023 1.0000
5.000 0.7867 0.00971 0.00347 -0.0480 0.1750 1.0000
5.250 0.8131 0.01013 0.00379 -0.0478 0.1475 1.0000
5.500 0.8393 0.01057 0.00414 -0.0476 0.1218 1.0000
5.750 0.8654 0.01103 0.00452 -0.0474 0.0987 1.0000
6.000 0.8914 0.01153 0.00496 -0.0472 0.0782 1.0000
6.250 0.9170 0.01209 0.00544 -0.0469 0.0593 1.0000
6.500 0.9424 0.01272 0.00605 -0.0466 0.0437 1.0000
6.750 0.9676 0.01336 0.00668 -0.0462 0.0319 1.0000
7.000 0.9923 0.01414 0.00747 -0.0458 0.0222 1.0000
7.250 1.0166 0.01502 0.00839 -0.0453 0.0157 1.0000
7.500 1.0402 0.01606 0.00958 -0.0446 0.0125 1.0000
7.750 1.0638 0.01702 0.01064 -0.0439 0.0105 1.0000
8.000 1.0829 0.01904 0.01286 -0.0427 0.0091 1.0000
8.250 1.1019 0.02104 0.01510 -0.0416 0.0083 1.0000
8.500 1.1254 0.02181 0.01603 -0.0410 0.0076 1.0000
8.750 1.1460 0.02326 0.01766 -0.0401 0.0071 1.0000
9.000 1.1652 0.02501 0.01962 -0.0391 0.0067 1.0000
9.250 1.1833 0.02685 0.02168 -0.0380 0.0064 1.0000
9.500 1.2003 0.02871 0.02377 -0.0370 0.0060 1.0000
9.750 1.2154 0.03072 0.02598 -0.0359 0.0057 1.0000
10.000 1.2259 0.03338 0.02890 -0.0346 0.0054 1.0000
10.250 1.2290 0.03705 0.03292 -0.0329 0.0053 1.0000
10.500 1.2258 0.04113 0.03736 -0.0311 0.0052 1.0000
10.750 1.2177 0.04496 0.04150 -0.0293 0.0052 1.0000
11.000 1.2047 0.04848 0.04526 -0.0277 0.0052 1.0000
11.250 1.1889 0.05306 0.05006 -0.0287 0.0052 1.0000
11.500 1.1749 0.05865 0.05586 -0.0321 0.0052 1.0000
11.750 1.1594 0.06590 0.06332 -0.0379 0.0053 1.0000
12.000 1.1435 0.07450 0.07211 -0.0449 0.0054 1.0000
12.250 1.1226 0.08501 0.08281 -0.0528 0.0055 1.0000
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Polar data table (+)
Polar graphs
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