AG13 (ag13-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 200,000 Max Cl/Cd: 62.12 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag13-il-200000.txt Download as CSV file: xf-ag13-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5461 0.09873 0.09533 0.0147 1.0000 0.0321
-7.750 -0.5415 0.09506 0.09169 0.0125 1.0000 0.0332
-7.500 -0.5370 0.09131 0.08798 0.0096 1.0000 0.0345
-7.250 -0.5297 0.08716 0.08387 0.0039 1.0000 0.0359
-7.000 -0.5103 0.08172 0.07843 -0.0088 1.0000 0.0371
-6.750 -0.4894 0.07602 0.07267 -0.0179 1.0000 0.0374
-6.500 -0.4742 0.06859 0.06518 -0.0253 1.0000 0.0378
-6.250 -0.4709 0.06454 0.06120 -0.0230 1.0000 0.0393
-6.000 -0.4565 0.06144 0.05811 -0.0237 1.0000 0.0410
-5.750 -0.4360 0.05708 0.05367 -0.0277 1.0000 0.0437
-5.500 -0.3936 0.05052 0.04645 -0.0396 1.0000 0.0500
-5.250 -0.3830 0.04483 0.04097 -0.0401 1.0000 0.0530
-5.000 -0.3522 0.04070 0.03620 -0.0447 1.0000 0.0639
-4.750 -0.3336 0.03725 0.03296 -0.0446 1.0000 0.0666
-4.500 -0.2944 0.01941 0.01501 -0.0445 1.0000 0.0780
-4.250 -0.2677 0.02466 0.01883 -0.0473 1.0000 0.0360
-4.000 -0.2393 0.02040 0.01402 -0.0477 1.0000 0.0316
-3.750 -0.2101 0.01745 0.01048 -0.0472 1.0000 0.0295
-3.500 -0.1823 0.01563 0.00838 -0.0468 1.0000 0.0301
-3.250 -0.1550 0.01427 0.00687 -0.0462 1.0000 0.0328
-3.000 -0.1281 0.01320 0.00568 -0.0458 1.0000 0.0392
-2.750 -0.1010 0.01207 0.00456 -0.0454 1.0000 0.0479
-2.500 -0.0735 0.01106 0.00359 -0.0452 1.0000 0.0766
-2.250 -0.0460 0.00987 0.00296 -0.0454 1.0000 0.1869
-2.000 -0.0196 0.00911 0.00278 -0.0456 1.0000 0.3406
-1.750 0.0062 0.00852 0.00269 -0.0453 1.0000 0.4828
-1.500 0.0305 0.00789 0.00262 -0.0445 1.0000 0.6366
-1.250 0.0512 0.00696 0.00245 -0.0419 1.0000 1.0000
-1.000 0.0781 0.00700 0.00234 -0.0417 1.0000 1.0000
-0.750 0.1048 0.00705 0.00227 -0.0416 1.0000 1.0000
-0.500 0.1314 0.00713 0.00225 -0.0415 1.0000 1.0000
-0.250 0.1580 0.00722 0.00226 -0.0414 1.0000 1.0000
0.000 0.1845 0.00734 0.00233 -0.0414 1.0000 1.0000
0.250 0.2349 0.00738 0.00231 -0.0462 0.9841 1.0000
0.500 0.2810 0.00738 0.00228 -0.0499 0.9643 1.0000
0.750 0.3224 0.00735 0.00223 -0.0523 0.9386 1.0000
1.000 0.3567 0.00735 0.00217 -0.0530 0.9049 1.0000
1.250 0.3847 0.00740 0.00213 -0.0522 0.8649 1.0000
1.500 0.4095 0.00753 0.00212 -0.0508 0.8216 1.0000
1.750 0.4337 0.00773 0.00215 -0.0494 0.7773 1.0000
2.000 0.4584 0.00797 0.00220 -0.0482 0.7322 1.0000
2.250 0.4834 0.00824 0.00228 -0.0471 0.6873 1.0000
2.500 0.5087 0.00853 0.00238 -0.0463 0.6432 1.0000
2.750 0.5343 0.00885 0.00251 -0.0455 0.5993 1.0000
3.000 0.5600 0.00918 0.00270 -0.0449 0.5556 1.0000
3.250 0.5858 0.00952 0.00288 -0.0444 0.5117 1.0000
3.500 0.6117 0.00988 0.00309 -0.0439 0.4680 1.0000
3.750 0.6376 0.01027 0.00333 -0.0434 0.4248 1.0000
4.000 0.6634 0.01068 0.00363 -0.0430 0.3817 1.0000
4.250 0.6893 0.01113 0.00393 -0.0427 0.3396 1.0000
4.500 0.7151 0.01160 0.00428 -0.0424 0.2989 1.0000
4.750 0.7408 0.01212 0.00467 -0.0421 0.2593 1.0000
5.000 0.7664 0.01267 0.00512 -0.0418 0.2229 1.0000
5.250 0.7917 0.01332 0.00565 -0.0415 0.1882 1.0000
5.500 0.8171 0.01397 0.00624 -0.0411 0.1568 1.0000
5.750 0.8422 0.01470 0.00690 -0.0408 0.1287 1.0000
6.000 0.8668 0.01556 0.00769 -0.0404 0.1054 1.0000
6.250 0.8915 0.01639 0.00850 -0.0399 0.0847 1.0000
6.500 0.9151 0.01756 0.00965 -0.0393 0.0678 1.0000
6.750 0.9391 0.01859 0.01076 -0.0387 0.0528 1.0000
7.000 0.9618 0.02008 0.01237 -0.0379 0.0420 1.0000
7.250 0.9830 0.02199 0.01432 -0.0371 0.0333 1.0000
7.500 1.0064 0.02362 0.01621 -0.0360 0.0289 1.0000
7.750 1.0270 0.02564 0.01831 -0.0353 0.0245 1.0000
8.000 1.0470 0.02835 0.02142 -0.0342 0.0221 1.0000
8.250 1.0662 0.03126 0.02476 -0.0329 0.0208 1.0000
8.500 1.0821 0.03489 0.02890 -0.0316 0.0200 1.0000
8.750 1.0930 0.03935 0.03394 -0.0302 0.0198 1.0000
9.000 1.0971 0.04468 0.03986 -0.0289 0.0201 1.0000
9.250 1.0942 0.05048 0.04619 -0.0280 0.0205 1.0000
9.500 1.0848 0.05631 0.05243 -0.0276 0.0210 1.0000
9.750 1.0698 0.06180 0.05823 -0.0278 0.0214 1.0000
10.000 1.0500 0.06687 0.06350 -0.0292 0.0216 1.0000
10.250 1.0301 0.07358 0.07038 -0.0349 0.0217 1.0000
10.500 1.0102 0.08311 0.08004 -0.0442 0.0219 1.0000
10.750 0.9892 0.09478 0.09177 -0.0536 0.0223 1.0000
11.000 0.9696 0.10542 0.10239 -0.0598 0.0229 1.0000
11.250 0.8472 0.09676 0.09383 -0.0419 0.0227 1.0000
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Polar data table (+)
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