ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 200,000 Max Cl/Cd: 66.2 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad10-il-200000.txt Download as CSV file: xf-arad10-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 10% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3685 0.10291 0.09925 -0.0214 1.0000 0.0542
-8.500 -0.3887 0.09934 0.09578 -0.0286 1.0000 0.0552
-8.250 -0.3926 0.09512 0.09162 -0.0307 1.0000 0.0555
-8.000 -0.3761 0.09221 0.08872 -0.0268 1.0000 0.0562
-7.750 -0.3693 0.08966 0.08620 -0.0257 1.0000 0.0570
-7.500 -0.3669 0.08710 0.08369 -0.0255 1.0000 0.0578
-7.250 -0.3672 0.08447 0.08112 -0.0258 1.0000 0.0589
-7.000 -0.3696 0.08175 0.07845 -0.0263 1.0000 0.0601
-6.750 -0.3740 0.07868 0.07541 -0.0280 1.0000 0.0619
-6.500 -0.3776 0.07123 0.06782 -0.0396 1.0000 0.0642
-6.250 -0.3760 0.06916 0.06582 -0.0363 1.0000 0.0646
-6.000 -0.3729 0.06734 0.06405 -0.0338 1.0000 0.0652
-5.750 -0.3629 0.06512 0.06184 -0.0332 0.9993 0.0663
-5.500 -0.3113 0.03991 0.03547 -0.0560 0.9959 0.0484
-5.250 -0.2724 0.03195 0.02678 -0.0617 0.9936 0.0470
-5.000 -0.2339 0.02569 0.01954 -0.0656 0.9904 0.0471
-4.750 -0.1943 0.02272 0.01603 -0.0685 0.9871 0.0491
-4.500 -0.1526 0.02178 0.01499 -0.0715 0.9840 0.0526
-4.250 -0.1130 0.02035 0.01328 -0.0740 0.9796 0.0574
-4.000 -0.0720 0.01942 0.01214 -0.0765 0.9750 0.0629
-3.750 -0.0292 0.01867 0.01139 -0.0796 0.9719 0.0700
-3.500 0.0110 0.01794 0.01061 -0.0821 0.9668 0.0777
-3.250 0.0523 0.01726 0.00983 -0.0847 0.9618 0.0865
-3.000 0.0961 0.01681 0.00935 -0.0878 0.9583 0.0957
-2.750 0.1347 0.01615 0.00875 -0.0898 0.9521 0.1045
-2.500 0.1721 0.01555 0.00812 -0.0915 0.9447 0.1142
-2.250 0.2083 0.01522 0.00776 -0.0927 0.9369 0.1250
-2.000 0.2406 0.01471 0.00733 -0.0932 0.9269 0.1366
-1.750 0.2698 0.01432 0.00696 -0.0930 0.9145 0.1490
-1.500 0.2973 0.01394 0.00658 -0.0921 0.8997 0.1626
-1.250 0.3231 0.01362 0.00625 -0.0908 0.8826 0.1773
-1.000 0.3489 0.01333 0.00596 -0.0896 0.8658 0.1935
-0.750 0.3753 0.01303 0.00571 -0.0888 0.8500 0.2120
-0.500 0.4019 0.01275 0.00550 -0.0880 0.8339 0.2342
-0.250 0.4288 0.01247 0.00530 -0.0874 0.8173 0.2647
0.000 0.4558 0.01201 0.00514 -0.0869 0.8006 0.3379
0.250 0.4749 0.01012 0.00485 -0.0840 0.7847 1.0000
0.500 0.5026 0.01020 0.00473 -0.0835 0.7673 1.0000
0.750 0.5302 0.01030 0.00465 -0.0830 0.7494 1.0000
1.000 0.5579 0.01041 0.00460 -0.0825 0.7308 1.0000
1.250 0.5855 0.01053 0.00458 -0.0821 0.7118 1.0000
1.500 0.6132 0.01067 0.00457 -0.0817 0.6924 1.0000
1.750 0.6407 0.01082 0.00457 -0.0813 0.6722 1.0000
2.000 0.6682 0.01098 0.00461 -0.0809 0.6500 1.0000
2.250 0.6957 0.01116 0.00465 -0.0806 0.6270 1.0000
2.500 0.7228 0.01136 0.00471 -0.0802 0.6026 1.0000
2.750 0.7499 0.01157 0.00478 -0.0798 0.5747 1.0000
3.000 0.7767 0.01182 0.00488 -0.0794 0.5442 1.0000
3.250 0.8030 0.01213 0.00500 -0.0789 0.5097 1.0000
3.500 0.8287 0.01252 0.00516 -0.0784 0.4700 1.0000
3.750 0.8540 0.01297 0.00537 -0.0779 0.4253 1.0000
4.000 0.8788 0.01352 0.00565 -0.0774 0.3828 1.0000
4.250 0.9036 0.01409 0.00599 -0.0770 0.3473 1.0000
4.500 0.9283 0.01470 0.00636 -0.0765 0.3208 1.0000
4.750 0.9537 0.01524 0.00677 -0.0762 0.3001 1.0000
5.000 0.9790 0.01578 0.00718 -0.0758 0.2837 1.0000
5.250 1.0041 0.01635 0.00762 -0.0754 0.2701 1.0000
5.500 1.0294 0.01687 0.00807 -0.0750 0.2582 1.0000
5.750 1.0551 0.01735 0.00853 -0.0747 0.2477 1.0000
6.000 1.0798 0.01796 0.00903 -0.0743 0.2386 1.0000
6.250 1.1054 0.01839 0.00949 -0.0740 0.2297 1.0000
6.500 1.1301 0.01904 0.01005 -0.0735 0.2224 1.0000
6.750 1.1554 0.01948 0.01053 -0.0731 0.2147 1.0000
7.000 1.1796 0.02020 0.01113 -0.0727 0.2079 1.0000
7.250 1.2046 0.02061 0.01165 -0.0723 0.2012 1.0000
7.500 1.2288 0.02120 0.01219 -0.0718 0.1952 1.0000
7.750 1.2529 0.02185 0.01287 -0.0713 0.1893 1.0000
8.000 1.2769 0.02235 0.01343 -0.0708 0.1832 1.0000
8.250 1.3005 0.02317 0.01414 -0.0703 0.1779 1.0000
8.500 1.3238 0.02370 0.01482 -0.0696 0.1727 1.0000
8.750 1.3466 0.02425 0.01541 -0.0690 0.1675 1.0000
9.000 1.3701 0.02524 0.01627 -0.0686 0.1625 1.0000
9.250 1.3916 0.02574 0.01699 -0.0676 0.1581 1.0000
9.500 1.4133 0.02634 0.01765 -0.0668 0.1534 1.0000
9.750 1.4353 0.02718 0.01842 -0.0662 0.1491 1.0000
10.000 1.4559 0.02800 0.01939 -0.0652 0.1451 1.0000
10.250 1.4757 0.02866 0.02018 -0.0641 0.1409 1.0000
10.500 1.4955 0.02934 0.02087 -0.0631 0.1371 1.0000
10.750 1.5164 0.03049 0.02199 -0.0624 0.1333 1.0000
11.000 1.5326 0.03123 0.02297 -0.0608 0.1298 1.0000
11.250 1.5493 0.03196 0.02380 -0.0594 0.1262 1.0000
11.500 1.5666 0.03276 0.02458 -0.0581 0.1230 1.0000
11.750 1.5840 0.03402 0.02590 -0.0570 0.1197 1.0000
12.000 1.5945 0.03494 0.02706 -0.0546 0.1167 1.0000
12.250 1.6059 0.03583 0.02806 -0.0525 0.1137 1.0000
12.500 1.6177 0.03670 0.02895 -0.0505 0.1110 1.0000
12.750 1.6349 0.03820 0.03041 -0.0496 0.1080 1.0000
13.000 1.6346 0.03941 0.03189 -0.0460 0.1061 1.0000
13.250 1.6373 0.04076 0.03344 -0.0431 0.1037 1.0000
13.500 1.6426 0.04206 0.03485 -0.0408 0.1013 1.0000
13.750 1.6511 0.04329 0.03612 -0.0391 0.0992 1.0000
14.000 1.6670 0.04507 0.03783 -0.0384 0.0965 1.0000
14.250 1.6621 0.04706 0.04011 -0.0357 0.0952 1.0000
14.500 1.6579 0.04931 0.04261 -0.0335 0.0934 1.0000
14.750 1.6558 0.05157 0.04507 -0.0318 0.0915 1.0000
15.000 1.6567 0.05366 0.04728 -0.0305 0.0897 1.0000
15.250 1.6619 0.05546 0.04911 -0.0296 0.0880 1.0000
15.500 1.6721 0.05749 0.05109 -0.0287 0.0859 1.0000
15.750 1.6603 0.06108 0.05496 -0.0277 0.0849 1.0000
16.000 1.6459 0.06509 0.05924 -0.0272 0.0839 1.0000
16.250 1.6307 0.06949 0.06391 -0.0273 0.0828 1.0000
16.500 1.6143 0.07431 0.06897 -0.0279 0.0817 1.0000
16.750 1.5977 0.07938 0.07424 -0.0289 0.0807 1.0000
17.000 1.5827 0.08451 0.07955 -0.0303 0.0796 1.0000
17.250 1.5721 0.08920 0.08438 -0.0318 0.0785 1.0000
17.500 1.5750 0.09190 0.08709 -0.0323 0.0772 1.0000
17.750 1.5769 0.09488 0.09006 -0.0323 0.0757 1.0000
18.000 1.5404 0.10422 0.09968 -0.0370 0.0753 1.0000
18.250 1.4901 0.11697 0.11275 -0.0445 0.0752 1.0000
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