ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 500,000 Max Cl/Cd: 82.3 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad10-il-500000-n5.txt Download as CSV file: xf-arad10-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7490 0.03061 0.02669 -0.0720 1.0000 0.0128
-10.250 -0.7292 0.02763 0.02337 -0.0731 1.0000 0.0130
-10.000 -0.7070 0.02559 0.02106 -0.0736 1.0000 0.0131
-9.750 -0.6843 0.02388 0.01913 -0.0739 1.0000 0.0133
-9.500 -0.6613 0.02249 0.01762 -0.0739 1.0000 0.0136
-9.250 -0.6381 0.02144 0.01646 -0.0736 1.0000 0.0138
-9.000 -0.6155 0.02053 0.01545 -0.0730 1.0000 0.0140
-8.750 -0.5847 0.01955 0.01433 -0.0742 0.9976 0.0143
-8.500 -0.5524 0.01863 0.01328 -0.0755 0.9952 0.0146
-8.250 -0.5201 0.01777 0.01230 -0.0768 0.9924 0.0149
-8.000 -0.4884 0.01699 0.01139 -0.0778 0.9883 0.0153
-7.750 -0.4558 0.01627 0.01056 -0.0790 0.9848 0.0156
-7.500 -0.4239 0.01564 0.00980 -0.0799 0.9802 0.0160
-7.250 -0.3926 0.01498 0.00907 -0.0808 0.9749 0.0164
-7.000 -0.3606 0.01445 0.00849 -0.0817 0.9700 0.0170
-6.750 -0.3309 0.01400 0.00798 -0.0820 0.9626 0.0175
-6.250 -0.2720 0.01321 0.00704 -0.0824 0.9472 0.0190
-6.000 -0.2435 0.01283 0.00662 -0.0823 0.9391 0.0200
-5.750 -0.2155 0.01252 0.00626 -0.0822 0.9293 0.0213
-5.500 -0.1875 0.01223 0.00591 -0.0819 0.9200 0.0227
-5.250 -0.1597 0.01192 0.00558 -0.0817 0.9096 0.0243
-5.000 -0.1316 0.01168 0.00527 -0.0815 0.8990 0.0264
-4.750 -0.1036 0.01143 0.00500 -0.0812 0.8881 0.0288
-4.500 -0.0754 0.01123 0.00475 -0.0810 0.8763 0.0316
-4.250 -0.0470 0.01104 0.00453 -0.0809 0.8642 0.0348
-4.000 -0.0186 0.01087 0.00433 -0.0808 0.8520 0.0384
-3.750 0.0098 0.01074 0.00413 -0.0806 0.8393 0.0421
-3.500 0.0385 0.01059 0.00395 -0.0806 0.8260 0.0459
-3.250 0.0673 0.01046 0.00378 -0.0805 0.8124 0.0498
-3.000 0.0961 0.01036 0.00363 -0.0805 0.7989 0.0549
-2.750 0.1249 0.01025 0.00350 -0.0805 0.7846 0.0608
-2.500 0.1535 0.01018 0.00337 -0.0804 0.7658 0.0664
-2.250 0.1817 0.01017 0.00324 -0.0802 0.7394 0.0725
-2.000 0.2102 0.01015 0.00314 -0.0801 0.7113 0.0797
-1.500 0.2677 0.01015 0.00298 -0.0801 0.6683 0.0956
-1.250 0.2966 0.01014 0.00292 -0.0802 0.6480 0.1044
-1.000 0.3256 0.01015 0.00288 -0.0802 0.6289 0.1135
-0.750 0.3546 0.01016 0.00285 -0.0803 0.6114 0.1233
-0.500 0.3835 0.01019 0.00283 -0.0804 0.5926 0.1337
-0.250 0.4123 0.01024 0.00281 -0.0805 0.5723 0.1441
0.000 0.4412 0.01029 0.00281 -0.0806 0.5529 0.1565
0.250 0.4700 0.01033 0.00283 -0.0807 0.5327 0.1715
0.500 0.4987 0.01040 0.00285 -0.0808 0.5086 0.1885
0.750 0.5273 0.01049 0.00289 -0.0809 0.4834 0.2087
1.000 0.5558 0.01056 0.00294 -0.0810 0.4586 0.2384
1.250 0.5842 0.01062 0.00302 -0.0812 0.4307 0.2897
1.750 0.6312 0.00922 0.00312 -0.0794 0.3706 1.0000
2.000 0.6592 0.00952 0.00323 -0.0794 0.3407 1.0000
2.250 0.6871 0.00983 0.00337 -0.0795 0.3121 1.0000
2.500 0.7150 0.01014 0.00351 -0.0795 0.2879 1.0000
2.750 0.7431 0.01040 0.00366 -0.0795 0.2699 1.0000
3.000 0.7711 0.01066 0.00381 -0.0796 0.2546 1.0000
3.500 0.8271 0.01115 0.00412 -0.0796 0.2283 1.0000
3.750 0.8551 0.01138 0.00429 -0.0797 0.2184 1.0000
4.000 0.8828 0.01164 0.00447 -0.0797 0.2082 1.0000
4.250 0.9107 0.01186 0.00465 -0.0797 0.2001 1.0000
4.500 0.9383 0.01212 0.00484 -0.0797 0.1924 1.0000
4.750 0.9660 0.01234 0.00504 -0.0797 0.1854 1.0000
5.000 0.9933 0.01261 0.00525 -0.0796 0.1784 1.0000
5.250 1.0209 0.01283 0.00546 -0.0796 0.1734 1.0000
5.500 1.0482 0.01308 0.00568 -0.0795 0.1678 1.0000
5.750 1.0750 0.01337 0.00593 -0.0794 0.1622 1.0000
6.000 1.1023 0.01360 0.00616 -0.0793 0.1575 1.0000
6.250 1.1291 0.01387 0.00642 -0.0792 0.1527 1.0000
6.500 1.1554 0.01419 0.00670 -0.0791 0.1479 1.0000
6.750 1.1823 0.01443 0.00696 -0.0789 0.1440 1.0000
7.000 1.2086 0.01471 0.00724 -0.0787 0.1393 1.0000
7.250 1.2344 0.01505 0.00755 -0.0785 0.1349 1.0000
7.500 1.2605 0.01533 0.00785 -0.0783 0.1313 1.0000
7.750 1.2863 0.01563 0.00817 -0.0780 0.1269 1.0000
8.000 1.3115 0.01599 0.00850 -0.0777 0.1228 1.0000
8.250 1.3367 0.01633 0.00886 -0.0774 0.1193 1.0000
8.500 1.3618 0.01665 0.00921 -0.0770 0.1155 1.0000
8.750 1.3863 0.01703 0.00958 -0.0766 0.1116 1.0000
9.000 1.4101 0.01745 0.01000 -0.0761 0.1081 1.0000
9.250 1.4344 0.01779 0.01039 -0.0756 0.1050 1.0000
9.500 1.4580 0.01819 0.01081 -0.0751 0.1014 1.0000
9.750 1.4806 0.01865 0.01127 -0.0744 0.0980 1.0000
10.000 1.5032 0.01909 0.01175 -0.0737 0.0952 1.0000
10.250 1.5256 0.01951 0.01221 -0.0729 0.0922 1.0000
10.500 1.5469 0.01999 0.01271 -0.0721 0.0890 1.0000
10.750 1.5668 0.02056 0.01329 -0.0710 0.0858 1.0000
11.000 1.5875 0.02102 0.01381 -0.0700 0.0836 1.0000
11.250 1.6071 0.02154 0.01437 -0.0689 0.0810 1.0000
11.500 1.6252 0.02212 0.01499 -0.0675 0.0783 1.0000
11.750 1.6414 0.02280 0.01569 -0.0659 0.0757 1.0000
12.000 1.6583 0.02338 0.01634 -0.0644 0.0740 1.0000
12.250 1.6728 0.02401 0.01705 -0.0624 0.0721 1.0000
12.500 1.6842 0.02475 0.01785 -0.0601 0.0701 1.0000
12.750 1.6947 0.02561 0.01875 -0.0577 0.0681 1.0000
13.000 1.7044 0.02660 0.01978 -0.0555 0.0661 1.0000
13.250 1.7165 0.02746 0.02074 -0.0536 0.0646 1.0000
13.500 1.7274 0.02846 0.02182 -0.0518 0.0629 1.0000
13.750 1.7372 0.02958 0.02301 -0.0500 0.0611 1.0000
14.000 1.7453 0.03088 0.02436 -0.0482 0.0592 1.0000
14.250 1.7527 0.03230 0.02585 -0.0466 0.0575 1.0000
14.500 1.7619 0.03364 0.02729 -0.0452 0.0558 1.0000
14.750 1.7691 0.03518 0.02892 -0.0438 0.0541 1.0000
15.000 1.7745 0.03696 0.03076 -0.0426 0.0524 1.0000
15.250 1.7779 0.03901 0.03289 -0.0414 0.0509 1.0000
15.500 1.7820 0.04107 0.03504 -0.0405 0.0496 1.0000
15.750 1.7860 0.04321 0.03729 -0.0397 0.0482 1.0000
16.000 1.7879 0.04565 0.03983 -0.0391 0.0468 1.0000
16.250 1.7876 0.04843 0.04271 -0.0387 0.0455 1.0000
16.500 1.7848 0.05161 0.04597 -0.0385 0.0444 1.0000
16.750 1.7802 0.05509 0.04956 -0.0385 0.0434 1.0000
17.000 1.7777 0.05843 0.05304 -0.0387 0.0426 1.0000
17.250 1.7731 0.06218 0.05691 -0.0391 0.0418 1.0000
17.500 1.7663 0.06633 0.06119 -0.0399 0.0410 1.0000
17.750 1.7569 0.07097 0.06595 -0.0409 0.0401 1.0000
18.000 1.7446 0.07618 0.07129 -0.0423 0.0394 1.0000
18.250 1.7293 0.08200 0.07724 -0.0441 0.0387 1.0000
18.500 1.7109 0.08843 0.08381 -0.0464 0.0381 1.0000
18.750 1.6898 0.09548 0.09099 -0.0490 0.0375 1.0000
19.000 1.6724 0.10203 0.09769 -0.0516 0.0371 1.0000
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