AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 50,000 Max Cl/Cd: 36.96 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-aquilasm-il-50000-n5.txt Download as CSV file: xf-aquilasm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AQUILA 9.3% smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3182 0.10121 0.09461 -0.0286 1.0000 0.0989
-8.000 -0.3276 0.09987 0.09342 -0.0307 1.0000 0.1017
-7.750 -0.3415 0.09879 0.09252 -0.0333 1.0000 0.1026
-7.500 -0.3382 0.09502 0.08885 -0.0330 1.0000 0.1038
-7.250 -0.3248 0.09098 0.08484 -0.0297 1.0000 0.1074
-7.000 -0.3250 0.08849 0.08247 -0.0294 1.0000 0.1107
-6.750 -0.3316 0.08652 0.08062 -0.0303 1.0000 0.1147
-6.500 -0.3493 0.08601 0.08018 -0.0343 1.0000 0.1175
-6.250 -0.3478 0.08237 0.07668 -0.0311 1.0000 0.1193
-6.000 -0.3479 0.07982 0.07423 -0.0277 1.0000 0.1222
-5.750 -0.3527 0.07794 0.07241 -0.0260 1.0000 0.1256
-5.500 -0.3455 0.07496 0.06936 -0.0314 0.9942 0.1343
-5.250 -0.3192 0.07087 0.06526 -0.0340 0.9847 0.1426
-5.000 -0.2925 0.06680 0.06109 -0.0389 0.9732 0.1551
-4.750 -0.2652 0.06308 0.05728 -0.0435 0.9619 0.1719
-4.500 -0.2032 0.05495 0.04815 -0.0559 0.9508 0.0714
-4.250 -0.1703 0.05071 0.04374 -0.0595 0.9424 0.0658
-3.750 -0.0992 0.04410 0.03597 -0.0654 0.9209 0.0579
-3.500 -0.0627 0.04074 0.03232 -0.0683 0.9134 0.0567
-3.250 -0.0323 0.03813 0.02936 -0.0695 0.9026 0.0555
-3.000 -0.0005 0.03578 0.02661 -0.0706 0.8923 0.0545
-2.750 0.0358 0.03350 0.02385 -0.0720 0.8840 0.0541
-2.500 0.0673 0.03176 0.02170 -0.0724 0.8733 0.0551
-2.250 0.0991 0.03045 0.01989 -0.0725 0.8626 0.0577
-2.000 0.1332 0.02873 0.01787 -0.0733 0.8538 0.0601
-1.750 0.1645 0.02738 0.01633 -0.0734 0.8434 0.0621
-1.500 0.1951 0.02638 0.01516 -0.0734 0.8324 0.0670
-1.250 0.2286 0.02552 0.01397 -0.0734 0.8227 0.0734
-1.000 0.2596 0.02452 0.01288 -0.0735 0.8127 0.0799
-0.750 0.2860 0.02393 0.01216 -0.0728 0.8009 0.0920
-0.500 0.3129 0.02333 0.01147 -0.0723 0.7897 0.1074
-0.250 0.3712 0.01964 0.01047 -0.0773 0.7828 1.0000
0.000 0.3959 0.01984 0.01017 -0.0762 0.7702 1.0000
0.250 0.4207 0.02003 0.01001 -0.0753 0.7580 1.0000
0.500 0.4460 0.02021 0.00990 -0.0745 0.7462 1.0000
0.750 0.4721 0.02036 0.00979 -0.0738 0.7351 1.0000
1.000 0.4980 0.02052 0.00973 -0.0731 0.7238 1.0000
1.250 0.5217 0.02076 0.00980 -0.0722 0.7113 1.0000
1.500 0.5459 0.02101 0.00989 -0.0713 0.6991 1.0000
1.750 0.5705 0.02123 0.00997 -0.0705 0.6873 1.0000
2.000 0.5960 0.02142 0.01003 -0.0697 0.6761 1.0000
2.250 0.6215 0.02161 0.01010 -0.0690 0.6649 1.0000
2.500 0.6450 0.02191 0.01032 -0.0681 0.6523 1.0000
2.750 0.6687 0.02220 0.01055 -0.0672 0.6399 1.0000
3.000 0.6929 0.02248 0.01078 -0.0664 0.6280 1.0000
3.250 0.7177 0.02273 0.01097 -0.0656 0.6164 1.0000
3.500 0.7434 0.02293 0.01109 -0.0648 0.6055 1.0000
3.750 0.7664 0.02329 0.01144 -0.0639 0.5928 1.0000
4.000 0.7895 0.02365 0.01183 -0.0630 0.5801 1.0000
4.250 0.8129 0.02400 0.01219 -0.0622 0.5678 1.0000
4.500 0.8365 0.02435 0.01254 -0.0613 0.5557 1.0000
4.750 0.8607 0.02467 0.01286 -0.0605 0.5440 1.0000
5.000 0.8856 0.02494 0.01317 -0.0597 0.5326 1.0000
5.250 0.9077 0.02540 0.01369 -0.0588 0.5197 1.0000
5.500 0.9298 0.02587 0.01422 -0.0579 0.5071 1.0000
5.750 0.9521 0.02634 0.01476 -0.0569 0.4947 1.0000
6.000 0.9746 0.02681 0.01533 -0.0560 0.4826 1.0000
6.250 0.9976 0.02725 0.01583 -0.0552 0.4708 1.0000
6.500 1.0215 0.02764 0.01625 -0.0543 0.4596 1.0000
6.750 1.0421 0.02824 0.01699 -0.0533 0.4470 1.0000
7.000 1.0625 0.02888 0.01780 -0.0523 0.4347 1.0000
7.250 1.0830 0.02952 0.01856 -0.0512 0.4226 1.0000
7.500 1.1040 0.03014 0.01929 -0.0502 0.4111 1.0000
7.750 1.1257 0.03070 0.01995 -0.0492 0.3997 1.0000
8.000 1.1465 0.03132 0.02073 -0.0482 0.3882 1.0000
8.250 1.1641 0.03215 0.02175 -0.0469 0.3760 1.0000
8.500 1.1817 0.03298 0.02275 -0.0456 0.3640 1.0000
8.750 1.1995 0.03377 0.02371 -0.0443 0.3522 1.0000
9.000 1.2175 0.03453 0.02464 -0.0430 0.3404 1.0000
9.250 1.2350 0.03524 0.02549 -0.0416 0.3281 1.0000
9.500 1.2512 0.03597 0.02633 -0.0401 0.3154 1.0000
9.750 1.2628 0.03688 0.02743 -0.0381 0.3017 1.0000
10.000 1.2722 0.03782 0.02852 -0.0360 0.2877 1.0000
10.250 1.2790 0.03883 0.02971 -0.0337 0.2735 1.0000
10.500 1.2823 0.03997 0.03098 -0.0311 0.2595 1.0000
10.750 1.2809 0.04132 0.03246 -0.0282 0.2462 1.0000
11.000 1.2781 0.04292 0.03420 -0.0256 0.2331 1.0000
11.250 1.2742 0.04480 0.03620 -0.0235 0.2203 1.0000
11.500 1.2694 0.04695 0.03847 -0.0218 0.2074 1.0000
11.750 1.2637 0.04941 0.04105 -0.0205 0.1945 1.0000
12.000 1.2574 0.05218 0.04391 -0.0196 0.1818 1.0000
12.250 1.2504 0.05524 0.04706 -0.0191 0.1693 1.0000
12.500 1.2426 0.05861 0.05048 -0.0190 0.1571 1.0000
12.750 1.2347 0.06218 0.05408 -0.0191 0.1457 1.0000
13.000 1.2269 0.06589 0.05777 -0.0194 0.1348 1.0000
13.250 1.2168 0.07027 0.06230 -0.0202 0.1246 1.0000
13.500 1.2070 0.07478 0.06689 -0.0211 0.1154 1.0000
13.750 1.1992 0.07899 0.07108 -0.0220 0.1072 1.0000
14.000 1.1900 0.08368 0.07584 -0.0233 0.0994 1.0000
14.250 1.1805 0.08866 0.08091 -0.0248 0.0926 1.0000
14.500 1.1740 0.09303 0.08525 -0.0261 0.0858 1.0000
14.750 1.1636 0.09867 0.09107 -0.0281 0.0807 1.0000
15.000 1.1569 0.10346 0.09588 -0.0299 0.0749 1.0000
15.250 1.1481 0.10899 0.10151 -0.0321 0.0705 1.0000
15.500 1.1366 0.11545 0.10818 -0.0350 0.0670 1.0000
15.750 1.1376 0.11857 0.11111 -0.0360 0.0613 1.0000
16.000 1.1221 0.12649 0.11934 -0.0400 0.0594 1.0000
16.250 1.1058 0.13497 0.12804 -0.0445 0.0582 1.0000
16.500 1.0850 0.14518 0.13843 -0.0501 0.0579 1.0000
16.750 1.0595 0.15772 0.15103 -0.0571 0.0586 1.0000
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Polar data table (+)
Polar graphs
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