ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 500,000 Max Cl/Cd: 82.15 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad10-il-500000.txt Download as CSV file: xf-arad10-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3006 0.08271 0.08055 -0.0326 1.0000 0.0312
-8.500 -0.2959 0.08018 0.07804 -0.0321 1.0000 0.0314
-8.250 -0.2942 0.07774 0.07564 -0.0313 1.0000 0.0317
-8.000 -0.5244 0.02866 0.02497 -0.0658 1.0000 0.0209
-7.750 -0.5066 0.02469 0.02043 -0.0664 0.9996 0.0214
-7.500 -0.4734 0.02180 0.01704 -0.0689 0.9979 0.0219
-7.250 -0.4388 0.01983 0.01468 -0.0710 0.9961 0.0223
-7.000 -0.4033 0.01837 0.01290 -0.0730 0.9945 0.0227
-6.750 -0.3688 0.01693 0.01135 -0.0748 0.9926 0.0234
-6.500 -0.3336 0.01616 0.01052 -0.0765 0.9900 0.0241
-6.250 -0.2975 0.01541 0.00967 -0.0782 0.9877 0.0250
-6.000 -0.2605 0.01468 0.00880 -0.0801 0.9858 0.0261
-5.750 -0.2233 0.01381 0.00785 -0.0822 0.9842 0.0274
-5.500 -0.1873 0.01337 0.00742 -0.0838 0.9812 0.0291
-5.250 -0.1530 0.01288 0.00684 -0.0850 0.9762 0.0312
-5.000 -0.1183 0.01240 0.00639 -0.0863 0.9718 0.0337
-4.750 -0.0871 0.01195 0.00590 -0.0868 0.9644 0.0369
-4.500 -0.0565 0.01171 0.00564 -0.0871 0.9570 0.0407
-4.250 -0.0289 0.01139 0.00533 -0.0867 0.9468 0.0449
-4.000 -0.0015 0.01115 0.00507 -0.0862 0.9374 0.0497
-3.750 0.0253 0.01102 0.00492 -0.0856 0.9264 0.0543
-3.500 0.0525 0.01076 0.00467 -0.0851 0.9153 0.0592
-3.250 0.0796 0.01067 0.00452 -0.0845 0.9043 0.0637
-3.000 0.1070 0.01045 0.00432 -0.0841 0.8925 0.0699
-2.750 0.1348 0.01028 0.00413 -0.0838 0.8796 0.0764
-2.500 0.1624 0.01017 0.00399 -0.0834 0.8643 0.0829
-2.250 0.1898 0.01000 0.00379 -0.0829 0.8454 0.0907
-2.000 0.2175 0.00991 0.00362 -0.0824 0.8260 0.0992
-1.750 0.2458 0.00984 0.00351 -0.0822 0.8083 0.1090
-1.500 0.2742 0.00975 0.00339 -0.0821 0.7908 0.1201
-1.250 0.3028 0.00969 0.00329 -0.0819 0.7733 0.1311
-0.750 0.3603 0.00963 0.00315 -0.0819 0.7396 0.1555
-0.250 0.4179 0.00957 0.00305 -0.0819 0.7047 0.1851
0.000 0.4468 0.00955 0.00302 -0.0819 0.6876 0.2049
0.250 0.4757 0.00950 0.00300 -0.0820 0.6701 0.2342
0.500 0.5045 0.00935 0.00300 -0.0822 0.6513 0.3011
0.750 0.5242 0.00744 0.00288 -0.0803 0.6338 1.0000
1.000 0.5530 0.00758 0.00288 -0.0803 0.6146 1.0000
1.250 0.5816 0.00774 0.00290 -0.0803 0.5938 1.0000
1.500 0.6101 0.00793 0.00294 -0.0803 0.5712 1.0000
1.750 0.6386 0.00811 0.00299 -0.0803 0.5474 1.0000
2.000 0.6668 0.00832 0.00305 -0.0803 0.5221 1.0000
2.250 0.6950 0.00855 0.00314 -0.0803 0.4931 1.0000
2.500 0.7228 0.00883 0.00324 -0.0802 0.4606 1.0000
2.750 0.7505 0.00915 0.00337 -0.0802 0.4261 1.0000
3.000 0.7778 0.00952 0.00353 -0.0801 0.3879 1.0000
3.250 0.8049 0.00992 0.00372 -0.0801 0.3485 1.0000
3.500 0.8320 0.01033 0.00393 -0.0800 0.3152 1.0000
4.000 0.8865 0.01106 0.00437 -0.0799 0.2688 1.0000
4.250 0.9138 0.01139 0.00459 -0.0799 0.2527 1.0000
4.500 0.9410 0.01172 0.00483 -0.0798 0.2392 1.0000
4.750 0.9684 0.01201 0.00506 -0.0798 0.2276 1.0000
5.000 0.9957 0.01229 0.00529 -0.0797 0.2179 1.0000
5.250 1.0225 0.01264 0.00556 -0.0796 0.2089 1.0000
5.500 1.0499 0.01287 0.00580 -0.0795 0.2017 1.0000
5.750 1.0763 0.01323 0.00609 -0.0794 0.1940 1.0000
6.000 1.1035 0.01348 0.00634 -0.0793 0.1878 1.0000
6.250 1.1300 0.01380 0.00663 -0.0791 0.1817 1.0000
6.500 1.1561 0.01415 0.00696 -0.0789 0.1759 1.0000
6.750 1.1829 0.01440 0.00722 -0.0787 0.1705 1.0000
7.000 1.2085 0.01479 0.00757 -0.0785 0.1648 1.0000
7.250 1.2343 0.01512 0.00791 -0.0782 0.1602 1.0000
7.500 1.2605 0.01540 0.00821 -0.0780 0.1553 1.0000
7.750 1.2852 0.01582 0.00859 -0.0776 0.1501 1.0000
8.000 1.3104 0.01618 0.00898 -0.0772 0.1460 1.0000
8.250 1.3360 0.01647 0.00930 -0.0769 0.1417 1.0000
8.500 1.3602 0.01689 0.00970 -0.0765 0.1370 1.0000
8.750 1.3838 0.01736 0.01018 -0.0759 0.1329 1.0000
9.000 1.4087 0.01765 0.01053 -0.0755 0.1293 1.0000
9.250 1.4324 0.01806 0.01094 -0.0749 0.1251 1.0000
9.500 1.4535 0.01869 0.01153 -0.0740 0.1207 1.0000
9.750 1.4777 0.01899 0.01192 -0.0735 0.1178 1.0000
10.000 1.5006 0.01938 0.01235 -0.0729 0.1142 1.0000
10.250 1.5212 0.01994 0.01289 -0.0719 0.1104 1.0000
10.500 1.5413 0.02052 0.01351 -0.0708 0.1072 1.0000
10.750 1.5631 0.02091 0.01398 -0.0699 0.1042 1.0000
11.000 1.5830 0.02141 0.01451 -0.0688 0.1011 1.0000
11.250 1.5992 0.02216 0.01524 -0.0672 0.0978 1.0000
11.500 1.6169 0.02276 0.01591 -0.0658 0.0952 1.0000
11.750 1.6351 0.02327 0.01651 -0.0644 0.0927 1.0000
12.000 1.6507 0.02390 0.01719 -0.0627 0.0902 1.0000
12.250 1.6601 0.02474 0.01805 -0.0600 0.0878 1.0000
12.500 1.6666 0.02585 0.01919 -0.0570 0.0853 1.0000
12.750 1.6811 0.02652 0.01999 -0.0553 0.0835 1.0000
13.000 1.6938 0.02734 0.02089 -0.0535 0.0813 1.0000
13.250 1.7044 0.02835 0.02195 -0.0516 0.0791 1.0000
13.500 1.7109 0.02970 0.02333 -0.0495 0.0770 1.0000
13.750 1.7161 0.03123 0.02493 -0.0473 0.0751 1.0000
14.000 1.7282 0.03229 0.02611 -0.0460 0.0734 1.0000
14.250 1.7385 0.03352 0.02744 -0.0447 0.0714 1.0000
14.500 1.7461 0.03502 0.02900 -0.0434 0.0695 1.0000
14.750 1.7486 0.03703 0.03105 -0.0419 0.0676 1.0000
15.000 1.7505 0.03921 0.03331 -0.0406 0.0658 1.0000
15.250 1.7588 0.04087 0.03510 -0.0398 0.0643 1.0000
15.500 1.7648 0.04279 0.03713 -0.0391 0.0627 1.0000
15.750 1.7681 0.04506 0.03949 -0.0385 0.0612 1.0000
16.000 1.7675 0.04784 0.04233 -0.0380 0.0597 1.0000
16.250 1.7608 0.05138 0.04594 -0.0376 0.0583 1.0000
16.500 1.7600 0.05436 0.04904 -0.0374 0.0572 1.0000
16.750 1.7606 0.05729 0.05212 -0.0376 0.0561 1.0000
17.000 1.7588 0.06061 0.05557 -0.0379 0.0549 1.0000
17.250 1.7550 0.06430 0.05938 -0.0384 0.0539 1.0000
17.500 1.7481 0.06849 0.06366 -0.0392 0.0529 1.0000
17.750 1.7379 0.07325 0.06851 -0.0404 0.0519 1.0000
18.000 1.7238 0.07865 0.07400 -0.0418 0.0510 1.0000
18.250 1.7106 0.08404 0.07950 -0.0433 0.0501 1.0000
18.500 1.7016 0.08900 0.08462 -0.0450 0.0494 1.0000
18.750 1.6903 0.09441 0.09018 -0.0469 0.0487 1.0000
19.000 1.6778 0.10008 0.09599 -0.0491 0.0479 1.0000
19.250 1.6641 0.10602 0.10205 -0.0515 0.0472 1.0000
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