AG14 (ag14-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 200,000 Max Cl/Cd: 62.17 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag14-il-200000.txt Download as CSV file: xf-ag14-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG14
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
------ -------- --------- --------- -------- -------- --------
0.250 0.2269 0.00734 0.00227 -0.0434 0.9971 1.0000
0.500 0.2772 0.00737 0.00226 -0.0481 0.9805 1.0000
0.750 0.3218 0.00735 0.00222 -0.0513 0.9574 1.0000
1.250 0.3940 0.00733 0.00210 -0.0535 0.8880 1.0000
1.500 0.4202 0.00742 0.00207 -0.0523 0.8414 1.0000
1.750 0.4443 0.00761 0.00209 -0.0507 0.7918 1.0000
2.000 0.4684 0.00786 0.00213 -0.0493 0.7402 1.0000
2.250 0.4929 0.00816 0.00220 -0.0481 0.6883 1.0000
2.500 0.5178 0.00849 0.00230 -0.0472 0.6371 1.0000
2.750 0.5431 0.00885 0.00243 -0.0464 0.5871 1.0000
3.000 0.5686 0.00921 0.00264 -0.0457 0.5384 1.0000
3.250 0.5943 0.00959 0.00283 -0.0452 0.4923 1.0000
3.500 0.6200 0.00999 0.00305 -0.0447 0.4483 1.0000
3.750 0.6459 0.01039 0.00329 -0.0443 0.4057 1.0000
4.000 0.6718 0.01081 0.00357 -0.0439 0.3644 1.0000
4.250 0.6977 0.01126 0.00393 -0.0436 0.3246 1.0000
4.500 0.7236 0.01173 0.00428 -0.0433 0.2856 1.0000
4.750 0.7494 0.01223 0.00467 -0.0430 0.2474 1.0000
5.000 0.7750 0.01280 0.00513 -0.0427 0.2125 1.0000
5.250 0.8005 0.01342 0.00564 -0.0424 0.1789 1.0000
5.500 0.8257 0.01412 0.00629 -0.0420 0.1507 1.0000
5.750 0.8508 0.01484 0.00695 -0.0417 0.1255 1.0000
6.000 0.8757 0.01567 0.00776 -0.0412 0.1047 1.0000
6.250 0.9004 0.01649 0.00857 -0.0408 0.0861 1.0000
6.500 0.9239 0.01768 0.00972 -0.0402 0.0700 1.0000
6.750 0.9483 0.01863 0.01079 -0.0397 0.0552 1.0000
7.000 0.9713 0.02003 0.01232 -0.0389 0.0435 1.0000
7.250 0.9929 0.02183 0.01417 -0.0381 0.0341 1.0000
7.500 1.0164 0.02336 0.01595 -0.0371 0.0288 1.0000
7.750 1.0353 0.02614 0.01888 -0.0362 0.0240 1.0000
8.000 1.0573 0.02816 0.02128 -0.0351 0.0219 1.0000
8.250 1.0763 0.03117 0.02473 -0.0339 0.0205 1.0000
8.500 1.0921 0.03485 0.02891 -0.0326 0.0198 1.0000
8.750 1.1026 0.03949 0.03414 -0.0312 0.0197 1.0000
9.000 1.1054 0.04522 0.04051 -0.0299 0.0201 1.0000
9.250 1.1005 0.05151 0.04737 -0.0291 0.0207 1.0000
9.500 1.0891 0.05768 0.05396 -0.0289 0.0212 1.0000
9.750 1.0723 0.06331 0.05987 -0.0295 0.0216 1.0000
10.000 1.0519 0.06881 0.06557 -0.0320 0.0218 1.0000
10.250 1.0319 0.07667 0.07359 -0.0397 0.0220 1.0000
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Polar data table (+)
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