AG12 (ag12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.63 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag12-il-1000000.txt Download as CSV file: xf-ag12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5958 0.11439 0.11280 0.0270 1.0000 0.0069
-9.250 -0.5916 0.11061 0.10903 0.0254 1.0000 0.0070
-9.000 -0.5876 0.10678 0.10522 0.0236 1.0000 0.0071
-5.750 -0.4270 0.01934 0.01584 -0.0456 1.0000 0.0060
-5.250 -0.3739 0.01437 0.01013 -0.0458 1.0000 0.0059
-5.000 -0.3476 0.01174 0.00716 -0.0459 1.0000 0.0069
-4.750 -0.3206 0.01114 0.00649 -0.0457 1.0000 0.0075
-4.500 -0.2936 0.01043 0.00569 -0.0455 1.0000 0.0079
-4.250 -0.2666 0.00969 0.00485 -0.0452 1.0000 0.0083
-4.000 -0.2396 0.00912 0.00420 -0.0449 1.0000 0.0088
-3.750 -0.2129 0.00876 0.00380 -0.0446 1.0000 0.0095
-3.500 -0.1861 0.00828 0.00325 -0.0442 1.0000 0.0098
-3.250 -0.1584 0.00735 0.00214 -0.0439 1.0000 0.0125
-3.000 -0.1318 0.00709 0.00186 -0.0436 1.0000 0.0161
-2.750 -0.1044 0.00668 0.00152 -0.0433 0.9999 0.0362
-2.500 -0.0672 0.00634 0.00132 -0.0454 0.9951 0.0743
-2.250 -0.0316 0.00602 0.00116 -0.0472 0.9868 0.1201
-2.000 0.0040 0.00568 0.00104 -0.0489 0.9739 0.1835
-1.750 0.0371 0.00540 0.00093 -0.0500 0.9515 0.2457
-1.500 0.0641 0.00523 0.00084 -0.0496 0.9172 0.3028
-1.250 0.0892 0.00514 0.00078 -0.0487 0.8786 0.3562
-1.000 0.1150 0.00511 0.00074 -0.0480 0.8400 0.4052
-0.750 0.1413 0.00506 0.00071 -0.0476 0.8021 0.4627
-0.500 0.1680 0.00503 0.00069 -0.0472 0.7643 0.5222
-0.250 0.1949 0.00495 0.00069 -0.0469 0.7270 0.5954
0.000 0.2216 0.00484 0.00070 -0.0466 0.6916 0.6823
0.250 0.2458 0.00450 0.00073 -0.0457 0.6576 0.8355
0.500 0.2725 0.00433 0.00070 -0.0450 0.6229 1.0000
0.750 0.3003 0.00449 0.00072 -0.0449 0.5885 1.0000
1.000 0.3280 0.00466 0.00074 -0.0448 0.5559 1.0000
1.250 0.3558 0.00482 0.00077 -0.0447 0.5241 1.0000
1.500 0.3836 0.00499 0.00081 -0.0446 0.4928 1.0000
1.750 0.4113 0.00517 0.00087 -0.0445 0.4620 1.0000
2.000 0.4390 0.00536 0.00093 -0.0444 0.4325 1.0000
2.250 0.4667 0.00554 0.00100 -0.0444 0.4031 1.0000
2.500 0.4944 0.00574 0.00109 -0.0443 0.3733 1.0000
2.750 0.5220 0.00594 0.00120 -0.0442 0.3453 1.0000
3.000 0.5496 0.00616 0.00130 -0.0441 0.3160 1.0000
3.250 0.5771 0.00638 0.00142 -0.0441 0.2897 1.0000
3.500 0.6045 0.00662 0.00156 -0.0440 0.2603 1.0000
3.750 0.6319 0.00686 0.00170 -0.0439 0.2353 1.0000
4.000 0.6592 0.00714 0.00189 -0.0438 0.2066 1.0000
4.250 0.6864 0.00741 0.00207 -0.0437 0.1832 1.0000
4.500 0.7135 0.00771 0.00227 -0.0436 0.1577 1.0000
5.000 0.7675 0.00836 0.00274 -0.0433 0.1113 1.0000
5.250 0.7943 0.00869 0.00301 -0.0432 0.0929 1.0000
5.500 0.8211 0.00904 0.00329 -0.0430 0.0750 1.0000
5.750 0.8476 0.00945 0.00361 -0.0429 0.0577 1.0000
6.000 0.8742 0.00984 0.00395 -0.0427 0.0439 1.0000
6.250 0.9006 0.01024 0.00431 -0.0425 0.0326 1.0000
6.500 0.9268 0.01070 0.00475 -0.0423 0.0229 1.0000
6.750 0.9531 0.01112 0.00515 -0.0421 0.0174 1.0000
7.000 0.9791 0.01161 0.00568 -0.0418 0.0124 1.0000
7.250 1.0042 0.01243 0.00656 -0.0413 0.0082 1.0000
7.500 1.0299 0.01294 0.00713 -0.0410 0.0069 1.0000
7.750 1.0547 0.01371 0.00797 -0.0405 0.0056 1.0000
8.000 1.0771 0.01511 0.00960 -0.0397 0.0048 1.0000
8.250 1.1018 0.01578 0.01035 -0.0393 0.0046 1.0000
8.500 1.1254 0.01670 0.01142 -0.0387 0.0044 1.0000
8.750 1.1483 0.01772 0.01259 -0.0381 0.0042 1.0000
9.000 1.1706 0.01884 0.01385 -0.0375 0.0040 1.0000
9.250 1.1923 0.02001 0.01517 -0.0368 0.0038 1.0000
9.500 1.2136 0.02119 0.01649 -0.0361 0.0036 1.0000
9.750 1.2346 0.02233 0.01777 -0.0354 0.0034 1.0000
10.000 1.2551 0.02347 0.01903 -0.0348 0.0032 1.0000
10.250 1.2733 0.02496 0.02067 -0.0340 0.0030 1.0000
10.500 1.2782 0.02885 0.02495 -0.0322 0.0027 1.0000
11.000 1.2619 0.03906 0.03611 -0.0282 0.0025 1.0000
11.250 1.2563 0.04221 0.03948 -0.0267 0.0025 1.0000
11.500 1.2402 0.04627 0.04375 -0.0264 0.0025 1.0000
11.750 1.2242 0.05214 0.04983 -0.0304 0.0025 1.0000
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Polar data table (+)
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