AG13 (ag13-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 50,000 Max Cl/Cd: 35.56 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag13-il-50000-n5.txt Download as CSV file: xf-ag13-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5713 0.12708 0.12010 0.0213 1.0000 0.0870
-9.250 -0.5753 0.12500 0.11812 0.0172 1.0000 0.0890
-9.000 -0.5776 0.12245 0.11565 0.0134 1.0000 0.0896
-8.750 -0.5687 0.11741 0.11066 0.0132 1.0000 0.0903
-8.500 -0.5572 0.11259 0.10584 0.0139 1.0000 0.0917
-8.250 -0.5501 0.10867 0.10195 0.0130 1.0000 0.0929
-8.000 -0.5446 0.10494 0.09827 0.0115 1.0000 0.0936
-7.750 -0.5405 0.10122 0.09460 0.0093 1.0000 0.0935
-7.500 -0.5334 0.09344 0.08679 0.0001 1.0000 0.0492
-7.250 -0.5242 0.08942 0.08279 0.0004 1.0000 0.0465
-7.000 -0.5151 0.08487 0.07828 -0.0031 1.0000 0.0444
-6.750 -0.5041 0.07985 0.07328 -0.0081 1.0000 0.0427
-6.500 -0.4904 0.07438 0.06780 -0.0140 1.0000 0.0415
-6.250 -0.4739 0.06855 0.06192 -0.0202 1.0000 0.0407
-6.000 -0.4556 0.06303 0.05631 -0.0256 1.0000 0.0408
-5.750 -0.4356 0.05773 0.05084 -0.0303 1.0000 0.0413
-5.500 -0.4132 0.05234 0.04521 -0.0348 1.0000 0.0417
-5.250 -0.3885 0.04692 0.03942 -0.0389 1.0000 0.0416
-5.000 -0.3619 0.04171 0.03372 -0.0422 1.0000 0.0412
-4.750 -0.3342 0.03716 0.02860 -0.0444 1.0000 0.0411
-4.500 -0.3062 0.03336 0.02423 -0.0457 1.0000 0.0418
-4.250 -0.2780 0.03014 0.02045 -0.0463 1.0000 0.0432
-4.000 -0.2495 0.02757 0.01724 -0.0464 1.0000 0.0475
-3.750 -0.2224 0.02544 0.01479 -0.0464 1.0000 0.0537
-3.500 -0.1952 0.02352 0.01256 -0.0458 1.0000 0.0592
-3.250 -0.1686 0.02191 0.01078 -0.0453 1.0000 0.0695
-3.000 -0.1421 0.02053 0.00924 -0.0447 1.0000 0.0872
-2.750 -0.1147 0.01921 0.00797 -0.0445 1.0000 0.1216
-2.500 -0.0869 0.01781 0.00683 -0.0447 1.0000 0.1978
-2.250 -0.0609 0.01655 0.00626 -0.0447 1.0000 0.3436
-2.000 -0.0385 0.01553 0.00590 -0.0434 1.0000 0.5157
-1.750 -0.0223 0.01442 0.00555 -0.0399 1.0000 0.7140
-1.500 0.0066 0.01376 0.00496 -0.0392 1.0000 1.0000
-1.250 0.0332 0.01377 0.00456 -0.0391 1.0000 1.0000
-1.000 0.0594 0.01380 0.00430 -0.0389 1.0000 1.0000
-0.750 0.0851 0.01385 0.00411 -0.0387 1.0000 1.0000
-0.500 0.1106 0.01391 0.00399 -0.0384 1.0000 1.0000
-0.250 0.1359 0.01401 0.00393 -0.0382 1.0000 1.0000
0.000 0.1610 0.01412 0.00391 -0.0380 1.0000 1.0000
0.250 0.1857 0.01427 0.00398 -0.0378 1.0000 1.0000
0.500 0.2101 0.01445 0.00411 -0.0376 1.0000 1.0000
0.750 0.2341 0.01468 0.00432 -0.0375 1.0000 1.0000
1.000 0.2713 0.01496 0.00459 -0.0400 0.9864 1.0000
1.250 0.3224 0.01519 0.00484 -0.0449 0.9579 1.0000
1.500 0.3690 0.01534 0.00504 -0.0484 0.9255 1.0000
1.750 0.4109 0.01546 0.00522 -0.0507 0.8884 1.0000
2.000 0.4478 0.01559 0.00540 -0.0517 0.8478 1.0000
2.250 0.4797 0.01575 0.00554 -0.0514 0.8049 1.0000
2.500 0.5074 0.01597 0.00571 -0.0503 0.7604 1.0000
2.750 0.5327 0.01626 0.00591 -0.0488 0.7152 1.0000
3.000 0.5571 0.01660 0.00622 -0.0471 0.6701 1.0000
3.250 0.5811 0.01700 0.00650 -0.0455 0.6254 1.0000
3.500 0.6050 0.01744 0.00685 -0.0441 0.5798 1.0000
3.750 0.6289 0.01793 0.00724 -0.0428 0.5347 1.0000
4.000 0.6527 0.01847 0.00768 -0.0417 0.4901 1.0000
4.250 0.6766 0.01906 0.00826 -0.0406 0.4459 1.0000
4.500 0.7006 0.01970 0.00884 -0.0397 0.4020 1.0000
4.750 0.7248 0.02040 0.00949 -0.0389 0.3589 1.0000
5.000 0.7492 0.02118 0.01023 -0.0383 0.3176 1.0000
5.250 0.7734 0.02205 0.01105 -0.0377 0.2787 1.0000
5.500 0.7971 0.02302 0.01205 -0.0371 0.2425 1.0000
5.750 0.8210 0.02407 0.01314 -0.0366 0.2082 1.0000
6.000 0.8443 0.02524 0.01433 -0.0360 0.1784 1.0000
6.250 0.8673 0.02655 0.01570 -0.0353 0.1523 1.0000
6.500 0.8898 0.02797 0.01718 -0.0347 0.1286 1.0000
6.750 0.9119 0.02961 0.01889 -0.0339 0.1100 1.0000
7.000 0.9333 0.03134 0.02076 -0.0332 0.0923 1.0000
7.250 0.9546 0.03345 0.02317 -0.0323 0.0793 1.0000
7.500 0.9747 0.03565 0.02553 -0.0315 0.0681 1.0000
7.750 0.9940 0.03792 0.02810 -0.0307 0.0584 1.0000
8.000 1.0125 0.04155 0.03226 -0.0296 0.0533 1.0000
8.250 1.0283 0.04422 0.03524 -0.0289 0.0470 1.0000
8.500 1.0402 0.04804 0.03954 -0.0282 0.0428 1.0000
8.750 1.0472 0.05299 0.04514 -0.0276 0.0409 1.0000
9.000 1.0485 0.05820 0.05090 -0.0273 0.0397 1.0000
9.250 1.0435 0.06365 0.05681 -0.0276 0.0391 1.0000
9.500 1.0320 0.06939 0.06289 -0.0287 0.0389 1.0000
9.750 1.0136 0.07530 0.06904 -0.0307 0.0393 1.0000
10.000 0.9920 0.08238 0.07624 -0.0357 0.0400 1.0000
10.250 0.9720 0.09128 0.08520 -0.0431 0.0410 1.0000
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Polar data table (+)
Polar graphs
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