AG13 (ag13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.95 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag13-il-1000000.txt Download as CSV file: xf-ag13-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5682 0.09690 0.09535 0.0184 1.0000 0.0067
-8.000 -0.5638 0.09318 0.09164 0.0163 1.0000 0.0068
-7.750 -0.5595 0.08940 0.08787 0.0140 1.0000 0.0069
-7.500 -0.5549 0.08550 0.08399 0.0112 1.0000 0.0071
-7.250 -0.5459 0.08103 0.07954 0.0066 1.0000 0.0072
-7.000 -0.5332 0.07604 0.07456 0.0006 1.0000 0.0074
-6.750 -0.5171 0.07054 0.06905 -0.0065 1.0000 0.0077
-6.500 -0.4972 0.06441 0.06289 -0.0146 1.0000 0.0080
-6.250 -0.4733 0.05750 0.05592 -0.0233 1.0000 0.0084
-6.000 -0.4454 0.05003 0.04834 -0.0315 1.0000 0.0089
-5.750 -0.4156 0.04465 0.04284 -0.0360 1.0000 0.0096
-5.250 -0.3619 0.01712 0.01342 -0.0477 1.0000 0.0059
-5.000 -0.3353 0.01361 0.00940 -0.0480 1.0000 0.0065
-4.750 -0.3087 0.01307 0.00880 -0.0479 1.0000 0.0072
-4.500 -0.2818 0.01219 0.00779 -0.0477 1.0000 0.0077
-4.250 -0.2549 0.01115 0.00659 -0.0474 1.0000 0.0081
-4.000 -0.2280 0.01015 0.00546 -0.0471 1.0000 0.0083
-3.750 -0.2014 0.00968 0.00491 -0.0467 1.0000 0.0090
-3.500 -0.1748 0.00906 0.00421 -0.0463 1.0000 0.0094
-3.250 -0.1480 0.00829 0.00334 -0.0459 1.0000 0.0095
-3.000 -0.1211 0.00768 0.00264 -0.0456 1.0000 0.0099
-2.750 -0.0936 0.00700 0.00184 -0.0453 1.0000 0.0141
-2.500 -0.0592 0.00663 0.00146 -0.0466 0.9970 0.0255
-2.250 -0.0225 0.00627 0.00125 -0.0485 0.9918 0.0623
-2.000 0.0136 0.00595 0.00110 -0.0504 0.9827 0.1085
-1.750 0.0480 0.00562 0.00098 -0.0518 0.9679 0.1747
-1.500 0.0782 0.00534 0.00087 -0.0522 0.9427 0.2437
-1.250 0.1040 0.00515 0.00080 -0.0515 0.9090 0.3119
-1.000 0.1290 0.00504 0.00075 -0.0507 0.8701 0.3789
-0.750 0.1547 0.00498 0.00071 -0.0500 0.8290 0.4453
-0.500 0.1810 0.00490 0.00069 -0.0496 0.7886 0.5224
0.000 0.2332 0.00455 0.00070 -0.0487 0.7110 0.7469
0.250 0.2573 0.00409 0.00068 -0.0474 0.6740 1.0000
0.500 0.2848 0.00427 0.00069 -0.0472 0.6367 1.0000
0.750 0.3124 0.00444 0.00070 -0.0471 0.6003 1.0000
1.000 0.3401 0.00461 0.00072 -0.0469 0.5656 1.0000
1.250 0.3677 0.00479 0.00075 -0.0468 0.5316 1.0000
1.500 0.3954 0.00497 0.00079 -0.0467 0.4987 1.0000
1.750 0.4230 0.00516 0.00085 -0.0466 0.4644 1.0000
2.000 0.4506 0.00536 0.00092 -0.0465 0.4319 1.0000
2.250 0.4782 0.00555 0.00099 -0.0464 0.4002 1.0000
2.500 0.5057 0.00577 0.00107 -0.0463 0.3681 1.0000
2.750 0.5332 0.00600 0.00117 -0.0462 0.3359 1.0000
3.000 0.5607 0.00622 0.00130 -0.0461 0.3066 1.0000
3.250 0.5880 0.00646 0.00143 -0.0460 0.2761 1.0000
3.500 0.6154 0.00670 0.00156 -0.0459 0.2482 1.0000
3.750 0.6427 0.00695 0.00172 -0.0458 0.2235 1.0000
4.000 0.6699 0.00723 0.00190 -0.0457 0.1956 1.0000
4.250 0.6971 0.00750 0.00209 -0.0456 0.1729 1.0000
4.500 0.7241 0.00781 0.00229 -0.0455 0.1478 1.0000
4.750 0.7511 0.00809 0.00251 -0.0454 0.1269 1.0000
5.000 0.7780 0.00842 0.00275 -0.0452 0.1058 1.0000
5.250 0.8048 0.00874 0.00303 -0.0451 0.0890 1.0000
5.500 0.8315 0.00910 0.00331 -0.0449 0.0722 1.0000
5.750 0.8581 0.00947 0.00362 -0.0447 0.0568 1.0000
6.000 0.8846 0.00984 0.00395 -0.0445 0.0447 1.0000
6.250 0.9109 0.01024 0.00431 -0.0443 0.0336 1.0000
6.500 0.9371 0.01068 0.00471 -0.0441 0.0241 1.0000
6.750 0.9633 0.01110 0.00514 -0.0439 0.0182 1.0000
7.000 0.9892 0.01161 0.00568 -0.0436 0.0128 1.0000
7.250 1.0142 0.01243 0.00656 -0.0431 0.0085 1.0000
7.500 1.0399 0.01294 0.00713 -0.0427 0.0071 1.0000
7.750 1.0645 0.01374 0.00800 -0.0423 0.0056 1.0000
8.000 1.0875 0.01498 0.00944 -0.0416 0.0049 1.0000
8.250 1.1118 0.01572 0.01029 -0.0411 0.0047 1.0000
8.500 1.1354 0.01664 0.01136 -0.0405 0.0044 1.0000
8.750 1.1584 0.01763 0.01249 -0.0399 0.0042 1.0000
9.000 1.1810 0.01868 0.01368 -0.0393 0.0040 1.0000
9.250 1.2032 0.01971 0.01484 -0.0386 0.0037 1.0000
9.500 1.2252 0.02072 0.01597 -0.0380 0.0034 1.0000
9.750 1.2463 0.02182 0.01718 -0.0374 0.0032 1.0000
10.000 1.2607 0.02428 0.01991 -0.0362 0.0029 1.0000
10.250 1.2530 0.03097 0.02731 -0.0333 0.0026 1.0000
10.500 1.2668 0.03285 0.02941 -0.0324 0.0026 1.0000
10.750 1.2732 0.03571 0.03254 -0.0311 0.0025 1.0000
11.000 1.2720 0.03925 0.03638 -0.0297 0.0025 1.0000
11.250 1.2605 0.04312 0.04051 -0.0280 0.0025 1.0000
11.500 1.2430 0.04747 0.04507 -0.0281 0.0025 1.0000
11.750 1.2247 0.05414 0.05196 -0.0331 0.0025 1.0000
12.000 1.2051 0.06385 0.06188 -0.0421 0.0026 1.0000
12.250 1.1777 0.07624 0.07443 -0.0519 0.0026 1.0000
14.000 1.0775 0.13330 0.13184 -0.0806 0.0028 1.0000
14.250 1.0645 0.14177 0.14034 -0.0844 0.0029 1.0000
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Polar data table (+)
Polar graphs
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