AG18 (ag18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 500,000 Max Cl/Cd: 81.83 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag18-il-500000.txt Download as CSV file: xf-ag18-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-4.250 -0.2410 0.01709 0.01238 -0.0513 1.0000 0.0142
-4.000 -0.2144 0.01628 0.01135 -0.0509 1.0000 0.0159
-3.750 -0.1874 0.01403 0.00876 -0.0506 1.0000 0.0156
-3.500 -0.1604 0.01211 0.00658 -0.0501 1.0000 0.0150
-3.250 -0.1335 0.01081 0.00512 -0.0497 1.0000 0.0151
-3.000 -0.1068 0.00991 0.00411 -0.0492 1.0000 0.0159
-2.750 -0.0792 0.00890 0.00296 -0.0490 1.0000 0.0187
-2.500 -0.0525 0.00846 0.00248 -0.0487 1.0000 0.0257
-2.250 -0.0249 0.00784 0.00197 -0.0486 1.0000 0.0603
-2.000 0.0047 0.00739 0.00179 -0.0492 0.9989 0.1300
-1.750 0.0445 0.00687 0.00164 -0.0521 0.9937 0.2393
-1.500 0.0826 0.00642 0.00156 -0.0545 0.9860 0.3545
-1.250 0.1193 0.00605 0.00147 -0.0564 0.9755 0.4547
-1.000 0.1540 0.00566 0.00142 -0.0579 0.9614 0.5657
-0.750 0.1840 0.00511 0.00137 -0.0581 0.9426 0.7249
-0.500 0.2101 0.00449 0.00126 -0.0567 0.9189 1.0000
-0.250 0.2362 0.00455 0.00119 -0.0559 0.8915 1.0000
0.000 0.2619 0.00464 0.00113 -0.0550 0.8624 1.0000
0.250 0.2877 0.00476 0.00109 -0.0542 0.8322 1.0000
0.500 0.3140 0.00489 0.00106 -0.0536 0.8011 1.0000
0.750 0.3405 0.00504 0.00105 -0.0530 0.7692 1.0000
1.000 0.3671 0.00521 0.00106 -0.0525 0.7365 1.0000
1.250 0.3939 0.00538 0.00107 -0.0521 0.7022 1.0000
1.500 0.4207 0.00557 0.00110 -0.0517 0.6662 1.0000
1.750 0.4476 0.00578 0.00116 -0.0514 0.6276 1.0000
2.000 0.4744 0.00601 0.00122 -0.0510 0.5862 1.0000
2.250 0.5013 0.00627 0.00130 -0.0508 0.5429 1.0000
2.500 0.5281 0.00655 0.00139 -0.0505 0.4982 1.0000
2.750 0.5550 0.00684 0.00151 -0.0503 0.4539 1.0000
3.000 0.5818 0.00715 0.00168 -0.0501 0.4116 1.0000
3.250 0.6087 0.00746 0.00183 -0.0500 0.3719 1.0000
3.500 0.6356 0.00778 0.00201 -0.0498 0.3357 1.0000
3.750 0.6624 0.00810 0.00220 -0.0497 0.3015 1.0000
4.000 0.6892 0.00843 0.00243 -0.0495 0.2692 1.0000
4.250 0.7160 0.00875 0.00266 -0.0494 0.2404 1.0000
4.500 0.7427 0.00910 0.00290 -0.0492 0.2101 1.0000
4.750 0.7694 0.00946 0.00318 -0.0490 0.1837 1.0000
5.000 0.7958 0.00985 0.00347 -0.0489 0.1569 1.0000
5.250 0.8222 0.01026 0.00383 -0.0487 0.1328 1.0000
5.500 0.8484 0.01071 0.00419 -0.0485 0.1103 1.0000
5.750 0.8746 0.01114 0.00457 -0.0483 0.0910 1.0000
6.000 0.9005 0.01163 0.00501 -0.0480 0.0739 1.0000
6.250 0.9262 0.01219 0.00551 -0.0477 0.0582 1.0000
6.500 0.9518 0.01272 0.00604 -0.0474 0.0456 1.0000
6.750 0.9771 0.01335 0.00670 -0.0471 0.0342 1.0000
7.000 1.0017 0.01416 0.00751 -0.0466 0.0243 1.0000
7.250 1.0270 0.01474 0.00812 -0.0462 0.0182 1.0000
7.500 1.0503 0.01591 0.00945 -0.0455 0.0138 1.0000
7.750 1.0741 0.01685 0.01048 -0.0449 0.0112 1.0000
8.000 1.0914 0.01944 0.01334 -0.0435 0.0091 1.0000
8.250 1.1163 0.01991 0.01390 -0.0431 0.0083 1.0000
8.500 1.1382 0.02117 0.01533 -0.0423 0.0075 1.0000
8.750 1.1589 0.02264 0.01702 -0.0414 0.0069 1.0000
9.000 1.1790 0.02410 0.01866 -0.0406 0.0064 1.0000
9.250 1.1972 0.02586 0.02059 -0.0396 0.0059 1.0000
9.500 1.2083 0.02917 0.02425 -0.0381 0.0055 1.0000
9.750 1.2109 0.03401 0.02960 -0.0360 0.0053 1.0000
10.000 1.2086 0.03898 0.03506 -0.0341 0.0052 1.0000
10.250 1.2043 0.04334 0.03980 -0.0325 0.0052 1.0000
10.500 1.1967 0.04721 0.04396 -0.0310 0.0052 1.0000
10.750 1.1838 0.05074 0.04770 -0.0297 0.0053 1.0000
11.000 1.1699 0.05515 0.05231 -0.0310 0.0053 1.0000
11.250 1.1568 0.06083 0.05819 -0.0350 0.0053 1.0000
11.500 1.1453 0.06772 0.06524 -0.0409 0.0053 1.0000
11.750 1.1331 0.07592 0.07360 -0.0479 0.0053 1.0000
12.000 1.1209 0.08455 0.08235 -0.0545 0.0054 1.0000
12.250 1.1069 0.09356 0.09146 -0.0604 0.0054 1.0000
12.500 1.0933 0.10229 0.10027 -0.0655 0.0055 1.0000
12.750 1.0750 0.11226 0.11032 -0.0707 0.0056 1.0000
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Polar data table (+)
Polar graphs
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