ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.66 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad10-il-1000000-n5.txt Download as CSV file: xf-arad10-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9342 0.03135 0.02813 -0.0725 1.0000 0.0098
-12.000 -0.9165 0.02782 0.02434 -0.0738 1.0000 0.0098
-11.750 -0.8951 0.02568 0.02201 -0.0744 1.0000 0.0099
-11.500 -0.8721 0.02401 0.02017 -0.0748 1.0000 0.0100
-11.250 -0.8479 0.02262 0.01864 -0.0751 1.0000 0.0101
-11.000 -0.8230 0.02143 0.01732 -0.0753 1.0000 0.0102
-10.750 -0.7975 0.02037 0.01613 -0.0755 1.0000 0.0103
-10.500 -0.7716 0.01944 0.01509 -0.0756 1.0000 0.0104
-10.250 -0.7454 0.01861 0.01415 -0.0756 1.0000 0.0105
-10.000 -0.7191 0.01786 0.01331 -0.0756 1.0000 0.0106
-9.750 -0.6889 0.01715 0.01250 -0.0764 0.9964 0.0107
-9.500 -0.6582 0.01623 0.01147 -0.0774 0.9928 0.0109
-9.250 -0.6278 0.01549 0.01065 -0.0782 0.9879 0.0112
-9.000 -0.5967 0.01490 0.01000 -0.0791 0.9833 0.0114
-8.750 -0.5671 0.01440 0.00944 -0.0795 0.9770 0.0117
-8.500 -0.5374 0.01395 0.00893 -0.0799 0.9708 0.0119
-8.250 -0.5091 0.01353 0.00844 -0.0799 0.9634 0.0122
-7.750 -0.4533 0.01277 0.00755 -0.0797 0.9479 0.0126
-7.500 -0.4258 0.01243 0.00715 -0.0794 0.9398 0.0129
-7.250 -0.3978 0.01211 0.00676 -0.0793 0.9312 0.0131
-7.000 -0.3700 0.01180 0.00638 -0.0791 0.9225 0.0134
-6.750 -0.3417 0.01144 0.00597 -0.0790 0.9128 0.0138
-6.500 -0.3135 0.01115 0.00563 -0.0788 0.9032 0.0143
-6.250 -0.2852 0.01091 0.00532 -0.0787 0.8924 0.0149
-6.000 -0.2566 0.01068 0.00504 -0.0787 0.8815 0.0155
-5.750 -0.2279 0.01048 0.00477 -0.0786 0.8702 0.0160
-5.500 -0.1993 0.01025 0.00449 -0.0786 0.8580 0.0170
-5.250 -0.1703 0.01005 0.00425 -0.0786 0.8455 0.0182
-5.000 -0.1413 0.00988 0.00402 -0.0786 0.8327 0.0197
-4.750 -0.1124 0.00971 0.00381 -0.0786 0.8198 0.0219
-4.500 -0.0833 0.00957 0.00362 -0.0787 0.8062 0.0245
-4.250 -0.0541 0.00944 0.00345 -0.0788 0.7925 0.0273
-4.000 -0.0249 0.00932 0.00330 -0.0788 0.7787 0.0304
-3.750 0.0044 0.00922 0.00316 -0.0789 0.7653 0.0335
-3.500 0.0336 0.00914 0.00303 -0.0790 0.7512 0.0364
-3.250 0.0628 0.00907 0.00291 -0.0791 0.7328 0.0398
-2.750 0.1206 0.00908 0.00271 -0.0792 0.6747 0.0472
-2.500 0.1498 0.00907 0.00262 -0.0793 0.6500 0.0517
-2.250 0.1790 0.00906 0.00255 -0.0795 0.6280 0.0576
-2.000 0.2082 0.00906 0.00249 -0.0796 0.6064 0.0640
-1.750 0.2374 0.00905 0.00244 -0.0798 0.5878 0.0712
-1.500 0.2668 0.00903 0.00239 -0.0799 0.5716 0.0783
-1.250 0.2960 0.00906 0.00236 -0.0801 0.5525 0.0852
-1.000 0.3253 0.00908 0.00234 -0.0802 0.5324 0.0942
-0.750 0.3545 0.00911 0.00233 -0.0804 0.5141 0.1021
-0.500 0.3837 0.00916 0.00233 -0.0806 0.4939 0.1103
-0.250 0.4127 0.00924 0.00234 -0.0807 0.4697 0.1200
0.000 0.4417 0.00934 0.00236 -0.0809 0.4447 0.1284
0.250 0.4707 0.00944 0.00240 -0.0810 0.4214 0.1393
0.500 0.4995 0.00957 0.00244 -0.0812 0.3938 0.1499
0.750 0.5281 0.00974 0.00251 -0.0813 0.3612 0.1636
1.000 0.5567 0.00990 0.00259 -0.0815 0.3321 0.1787
1.250 0.5854 0.01006 0.00268 -0.0816 0.3069 0.1954
1.500 0.6140 0.01019 0.00277 -0.0818 0.2840 0.2204
1.750 0.6426 0.01030 0.00287 -0.0820 0.2642 0.2529
2.000 0.6715 0.01026 0.00298 -0.0823 0.2503 0.3435
2.250 0.6918 0.00876 0.00305 -0.0808 0.2389 1.0000
2.500 0.7205 0.00895 0.00315 -0.0810 0.2259 1.0000
2.750 0.7492 0.00912 0.00325 -0.0811 0.2155 1.0000
3.000 0.7778 0.00931 0.00336 -0.0812 0.2061 1.0000
3.250 0.8064 0.00949 0.00348 -0.0813 0.1967 1.0000
3.500 0.8349 0.00967 0.00360 -0.0814 0.1893 1.0000
3.750 0.8634 0.00985 0.00373 -0.0815 0.1821 1.0000
4.000 0.8918 0.01004 0.00386 -0.0816 0.1753 1.0000
4.250 0.9201 0.01021 0.00400 -0.0817 0.1695 1.0000
4.500 0.9483 0.01041 0.00415 -0.0818 0.1638 1.0000
4.750 0.9766 0.01058 0.00430 -0.0818 0.1597 1.0000
5.000 1.0047 0.01077 0.00445 -0.0819 0.1545 1.0000
5.250 1.0325 0.01099 0.00463 -0.0819 0.1489 1.0000
5.500 1.0606 0.01116 0.00479 -0.0820 0.1457 1.0000
5.750 1.0884 0.01135 0.00497 -0.0820 0.1417 1.0000
6.000 1.1159 0.01159 0.00516 -0.0820 0.1365 1.0000
6.250 1.1435 0.01180 0.00536 -0.0820 0.1326 1.0000
6.500 1.1710 0.01200 0.00555 -0.0820 0.1291 1.0000
7.000 1.2251 0.01249 0.00600 -0.0819 0.1201 1.0000
7.250 1.2523 0.01271 0.00621 -0.0818 0.1172 1.0000
7.500 1.2790 0.01297 0.00646 -0.0817 0.1130 1.0000
7.750 1.3053 0.01327 0.00672 -0.0816 0.1083 1.0000
8.000 1.3319 0.01350 0.00697 -0.0814 0.1059 1.0000
8.250 1.3582 0.01377 0.00724 -0.0813 0.1025 1.0000
8.500 1.3839 0.01409 0.00753 -0.0810 0.0983 1.0000
8.750 1.4097 0.01438 0.00782 -0.0808 0.0954 1.0000
9.000 1.4354 0.01466 0.00812 -0.0806 0.0926 1.0000
9.250 1.4604 0.01500 0.00845 -0.0802 0.0891 1.0000
9.500 1.4850 0.01536 0.00880 -0.0798 0.0855 1.0000
9.750 1.5100 0.01567 0.00913 -0.0795 0.0832 1.0000
10.000 1.5342 0.01602 0.00949 -0.0791 0.0801 1.0000
10.250 1.5577 0.01644 0.00989 -0.0785 0.0768 1.0000
10.500 1.5814 0.01680 0.01028 -0.0780 0.0745 1.0000
10.750 1.6049 0.01716 0.01067 -0.0774 0.0725 1.0000
11.000 1.6275 0.01757 0.01109 -0.0767 0.0701 1.0000
11.250 1.6492 0.01803 0.01156 -0.0759 0.0675 1.0000
11.500 1.6708 0.01846 0.01201 -0.0751 0.0655 1.0000
11.750 1.6921 0.01888 0.01247 -0.0742 0.0635 1.0000
12.000 1.7122 0.01937 0.01297 -0.0731 0.0613 1.0000
12.250 1.7308 0.01993 0.01354 -0.0719 0.0587 1.0000
12.500 1.7495 0.02044 0.01409 -0.0706 0.0566 1.0000
12.750 1.7671 0.02099 0.01467 -0.0692 0.0544 1.0000
13.000 1.7825 0.02163 0.01533 -0.0674 0.0522 1.0000
13.250 1.7956 0.02231 0.01604 -0.0653 0.0502 1.0000
13.500 1.8069 0.02298 0.01676 -0.0628 0.0487 1.0000
13.750 1.8173 0.02377 0.01760 -0.0604 0.0469 1.0000
14.000 1.8269 0.02469 0.01855 -0.0580 0.0451 1.0000
14.250 1.8362 0.02568 0.01958 -0.0558 0.0434 1.0000
14.500 1.8472 0.02662 0.02059 -0.0540 0.0423 1.0000
14.750 1.8570 0.02769 0.02172 -0.0521 0.0409 1.0000
15.000 1.8652 0.02892 0.02300 -0.0503 0.0395 1.0000
15.250 1.8719 0.03033 0.02446 -0.0485 0.0381 1.0000
15.500 1.8795 0.03173 0.02593 -0.0469 0.0370 1.0000
15.750 1.8868 0.03321 0.02748 -0.0455 0.0359 1.0000
16.000 1.8921 0.03493 0.02927 -0.0441 0.0346 1.0000
16.250 1.8950 0.03695 0.03135 -0.0428 0.0332 1.0000
16.500 1.8971 0.03914 0.03360 -0.0417 0.0320 1.0000
16.750 1.9003 0.04130 0.03585 -0.0409 0.0311 1.0000
17.000 1.9017 0.04371 0.03835 -0.0402 0.0302 1.0000
17.250 1.9012 0.04643 0.04115 -0.0396 0.0293 1.0000
17.500 1.8982 0.04955 0.04435 -0.0393 0.0284 1.0000
17.750 1.8927 0.05305 0.04795 -0.0392 0.0275 1.0000
18.000 1.8883 0.05655 0.05156 -0.0394 0.0269 1.0000
18.250 1.8821 0.06044 0.05555 -0.0398 0.0261 1.0000
18.500 1.8736 0.06475 0.05997 -0.0405 0.0254 1.0000
18.750 1.8617 0.06963 0.06497 -0.0415 0.0248 1.0000
19.000 1.8468 0.07510 0.07055 -0.0429 0.0243 1.0000
19.250 1.8290 0.08117 0.07676 -0.0447 0.0238 1.0000
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