ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 100,000 Max Cl/Cd: 41.81 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad13-il-100000.txt Download as CSV file: xf-arad13-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3810 0.09771 0.09291 -0.0132 1.0000 0.1268
-8.000 -0.4224 0.09359 0.08888 -0.0255 1.0000 0.1311
-7.750 -0.4161 0.08846 0.08382 -0.0258 1.0000 0.1326
-7.500 -0.3951 0.08570 0.08112 -0.0213 1.0000 0.1348
-7.250 -0.3853 0.08267 0.07813 -0.0211 1.0000 0.1383
-7.000 -0.4101 0.07686 0.07206 -0.0355 1.0000 0.1470
-6.750 -0.3922 0.07329 0.06874 -0.0306 1.0000 0.1489
-6.500 -0.3803 0.07130 0.06686 -0.0273 1.0000 0.1527
-6.250 -0.4025 0.05255 0.04690 -0.0411 1.0000 0.1055
-6.000 -0.3979 0.05072 0.04524 -0.0384 1.0000 0.1067
-5.750 -0.3937 0.04770 0.04213 -0.0366 1.0000 0.1022
-5.500 -0.3884 0.04401 0.03815 -0.0357 1.0000 0.1012
-5.250 -0.3720 0.03980 0.03346 -0.0364 0.9987 0.1017
-5.000 -0.3261 0.03413 0.02666 -0.0416 0.9928 0.1056
-4.750 -0.2807 0.03267 0.02537 -0.0457 0.9846 0.1115
-4.500 -0.2333 0.02980 0.02178 -0.0499 0.9770 0.1187
-4.250 -0.1847 0.02850 0.02050 -0.0543 0.9695 0.1270
-4.000 -0.1383 0.02674 0.01843 -0.0580 0.9602 0.1354
-3.750 -0.0851 0.02551 0.01687 -0.0626 0.9540 0.1464
-3.500 -0.0421 0.02424 0.01568 -0.0656 0.9426 0.1565
-3.250 0.0026 0.02309 0.01442 -0.0685 0.9323 0.1686
-3.000 0.0443 0.02217 0.01339 -0.0706 0.9204 0.1825
-2.750 0.0783 0.02155 0.01274 -0.0712 0.9047 0.1969
-2.500 0.1089 0.02087 0.01213 -0.0710 0.8885 0.2118
-2.250 0.1370 0.02030 0.01160 -0.0703 0.8718 0.2282
-2.000 0.1633 0.01979 0.01114 -0.0691 0.8549 0.2468
-1.750 0.1887 0.01932 0.01071 -0.0677 0.8383 0.2686
-1.500 0.2135 0.01883 0.01031 -0.0661 0.8224 0.2954
-1.250 0.2380 0.01829 0.00996 -0.0646 0.8061 0.3337
-1.000 0.2613 0.01735 0.00971 -0.0633 0.7893 0.4462
-0.750 0.2950 0.01573 0.00946 -0.0614 0.7724 1.0000
-0.500 0.3203 0.01583 0.00926 -0.0602 0.7556 1.0000
-0.250 0.3459 0.01593 0.00912 -0.0591 0.7391 1.0000
0.000 0.3717 0.01603 0.00898 -0.0581 0.7228 1.0000
0.250 0.3978 0.01613 0.00886 -0.0571 0.7066 1.0000
0.500 0.4242 0.01623 0.00876 -0.0562 0.6900 1.0000
0.750 0.4509 0.01636 0.00871 -0.0555 0.6721 1.0000
1.000 0.4777 0.01649 0.00868 -0.0548 0.6541 1.0000
1.250 0.5047 0.01663 0.00865 -0.0541 0.6358 1.0000
1.500 0.5317 0.01678 0.00864 -0.0535 0.6171 1.0000
1.750 0.5589 0.01694 0.00864 -0.0530 0.5982 1.0000
2.000 0.5860 0.01712 0.00865 -0.0524 0.5787 1.0000
2.250 0.6131 0.01732 0.00867 -0.0519 0.5589 1.0000
2.500 0.6403 0.01754 0.00873 -0.0514 0.5385 1.0000
2.750 0.6673 0.01780 0.00887 -0.0510 0.5164 1.0000
3.000 0.6943 0.01809 0.00901 -0.0506 0.4946 1.0000
3.250 0.7213 0.01841 0.00918 -0.0502 0.4734 1.0000
3.500 0.7482 0.01878 0.00938 -0.0499 0.4531 1.0000
3.750 0.7750 0.01919 0.00962 -0.0496 0.4338 1.0000
4.000 0.8018 0.01964 0.00993 -0.0493 0.4157 1.0000
4.250 0.8286 0.02012 0.01028 -0.0491 0.3986 1.0000
4.500 0.8553 0.02065 0.01070 -0.0489 0.3830 1.0000
4.750 0.8820 0.02121 0.01115 -0.0487 0.3690 1.0000
5.000 0.9088 0.02180 0.01157 -0.0485 0.3567 1.0000
5.250 0.9354 0.02237 0.01209 -0.0483 0.3442 1.0000
5.500 0.9618 0.02304 0.01275 -0.0482 0.3330 1.0000
5.750 0.9889 0.02373 0.01322 -0.0481 0.3237 1.0000
6.000 1.0145 0.02440 0.01400 -0.0479 0.3134 1.0000
6.250 1.0416 0.02517 0.01459 -0.0478 0.3054 1.0000
6.500 1.0667 0.02589 0.01546 -0.0476 0.2964 1.0000
6.750 1.0940 0.02670 0.01605 -0.0476 0.2894 1.0000
7.000 1.1180 0.02753 0.01710 -0.0472 0.2814 1.0000
7.250 1.1443 0.02828 0.01777 -0.0471 0.2747 1.0000
7.500 1.1691 0.02929 0.01883 -0.0469 0.2683 1.0000
7.750 1.1929 0.03016 0.01982 -0.0465 0.2615 1.0000
8.000 1.2200 0.03105 0.02054 -0.0466 0.2560 1.0000
8.250 1.2415 0.03221 0.02194 -0.0460 0.2501 1.0000
8.500 1.2644 0.03316 0.02301 -0.0455 0.2442 1.0000
8.750 1.2912 0.03412 0.02381 -0.0456 0.2394 1.0000
9.000 1.3102 0.03552 0.02549 -0.0448 0.2343 1.0000
9.250 1.3304 0.03670 0.02684 -0.0441 0.2291 1.0000
9.500 1.3548 0.03763 0.02773 -0.0438 0.2245 1.0000
9.750 1.3753 0.03920 0.02938 -0.0433 0.2203 1.0000
10.000 1.3888 0.04084 0.03137 -0.0419 0.2157 1.0000
10.250 1.4079 0.04209 0.03272 -0.0412 0.2114 1.0000
10.500 1.4335 0.04312 0.03364 -0.0412 0.2076 1.0000
10.750 1.4429 0.04532 0.03615 -0.0396 0.2040 1.0000
11.000 1.4468 0.04760 0.03879 -0.0374 0.2002 1.0000
11.250 1.4601 0.04924 0.04056 -0.0362 0.1966 1.0000
11.500 1.4821 0.05031 0.04159 -0.0358 0.1932 1.0000
11.750 1.4959 0.05248 0.04384 -0.0349 0.1902 1.0000
12.000 1.4737 0.05615 0.04801 -0.0307 0.1879 1.0000
12.250 1.4442 0.06018 0.05242 -0.0262 0.1860 1.0000
12.500 1.3926 0.06566 0.05822 -0.0214 0.1851 1.0000
13.250 1.4527 0.06952 0.06203 -0.0201 0.1763 1.0000
13.500 0.8861 0.17731 0.17075 -0.0754 0.2241 1.0000
13.750 0.9256 0.18159 0.17509 -0.0730 0.2224 1.0000
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Polar data table (+)
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