ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 200,000 Max Cl/Cd: 61.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad10-il-200000-n5.txt Download as CSV file: xf-arad10-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4082 0.09435 0.09059 -0.0243 1.0000 0.0225
-7.500 -0.4739 0.02911 0.02358 -0.0659 1.0000 0.0222
-7.250 -0.4495 0.02608 0.02003 -0.0670 0.9986 0.0229
-7.000 -0.4153 0.02515 0.01902 -0.0690 0.9954 0.0237
-6.750 -0.3811 0.02365 0.01726 -0.0711 0.9922 0.0248
-6.500 -0.3471 0.02175 0.01494 -0.0729 0.9884 0.0261
-6.250 -0.3119 0.02050 0.01349 -0.0749 0.9852 0.0270
-6.000 -0.2762 0.01966 0.01256 -0.0768 0.9821 0.0282
-5.750 -0.2424 0.01871 0.01142 -0.0781 0.9770 0.0298
-5.500 -0.2071 0.01789 0.01048 -0.0797 0.9727 0.0317
-5.250 -0.1728 0.01734 0.00987 -0.0811 0.9675 0.0343
-5.000 -0.1394 0.01674 0.00918 -0.0823 0.9610 0.0372
-4.750 -0.1041 0.01618 0.00853 -0.0837 0.9560 0.0406
-4.500 -0.0731 0.01574 0.00807 -0.0843 0.9470 0.0441
-4.250 -0.0394 0.01531 0.00757 -0.0853 0.9405 0.0488
-4.000 -0.0096 0.01501 0.00726 -0.0855 0.9301 0.0537
-3.750 0.0213 0.01469 0.00693 -0.0859 0.9212 0.0588
-3.500 0.0508 0.01440 0.00657 -0.0859 0.9105 0.0645
-3.250 0.0796 0.01415 0.00633 -0.0859 0.8994 0.0702
-3.000 0.1085 0.01387 0.00604 -0.0857 0.8886 0.0762
-2.750 0.1367 0.01367 0.00579 -0.0855 0.8765 0.0829
-2.500 0.1648 0.01345 0.00559 -0.0852 0.8639 0.0900
-2.250 0.1930 0.01326 0.00536 -0.0849 0.8514 0.0979
-2.000 0.2210 0.01310 0.00519 -0.0846 0.8385 0.1069
-1.750 0.2490 0.01295 0.00502 -0.0843 0.8246 0.1161
-1.500 0.2765 0.01285 0.00484 -0.0838 0.8065 0.1265
-1.250 0.3038 0.01274 0.00469 -0.0833 0.7829 0.1378
-1.000 0.3311 0.01266 0.00454 -0.0827 0.7591 0.1496
-0.750 0.3589 0.01261 0.00442 -0.0824 0.7390 0.1630
-0.500 0.3869 0.01256 0.00433 -0.0822 0.7192 0.1781
-0.250 0.4150 0.01251 0.00425 -0.0820 0.6994 0.1957
0.000 0.4431 0.01247 0.00420 -0.0818 0.6795 0.2176
0.250 0.4712 0.01241 0.00416 -0.0817 0.6601 0.2480
0.500 0.4991 0.01226 0.00414 -0.0817 0.6407 0.3111
1.000 0.5464 0.01061 0.00396 -0.0790 0.6014 1.0000
1.250 0.5744 0.01079 0.00397 -0.0789 0.5791 1.0000
1.500 0.6022 0.01100 0.00401 -0.0787 0.5562 1.0000
1.750 0.6299 0.01122 0.00406 -0.0785 0.5309 1.0000
2.250 0.6845 0.01175 0.00422 -0.0781 0.4746 1.0000
2.500 0.7115 0.01206 0.00435 -0.0779 0.4436 1.0000
2.750 0.7382 0.01241 0.00449 -0.0776 0.4101 1.0000
3.000 0.7647 0.01280 0.00467 -0.0774 0.3768 1.0000
3.250 0.7911 0.01320 0.00488 -0.0772 0.3459 1.0000
3.500 0.8174 0.01362 0.00512 -0.0770 0.3187 1.0000
3.750 0.8438 0.01402 0.00537 -0.0768 0.2958 1.0000
4.000 0.8701 0.01442 0.00565 -0.0766 0.2777 1.0000
4.250 0.8965 0.01480 0.00593 -0.0764 0.2625 1.0000
4.500 0.9228 0.01518 0.00623 -0.0762 0.2492 1.0000
4.750 0.9489 0.01558 0.00655 -0.0759 0.2378 1.0000
5.000 0.9751 0.01595 0.00686 -0.0757 0.2274 1.0000
5.250 1.0012 0.01632 0.00719 -0.0755 0.2184 1.0000
5.500 1.0268 0.01673 0.00755 -0.0752 0.2099 1.0000
5.750 1.0527 0.01709 0.00791 -0.0749 0.2026 1.0000
6.000 1.0781 0.01750 0.00828 -0.0746 0.1953 1.0000
6.250 1.1034 0.01790 0.00868 -0.0742 0.1890 1.0000
6.500 1.1287 0.01830 0.00908 -0.0739 0.1828 1.0000
7.000 1.1781 0.01916 0.00995 -0.0730 0.1719 1.0000
7.250 1.2024 0.01960 0.01040 -0.0725 0.1665 1.0000
7.500 1.2258 0.02013 0.01089 -0.0719 0.1618 1.0000
7.750 1.2502 0.02054 0.01138 -0.0714 0.1571 1.0000
8.000 1.2736 0.02101 0.01188 -0.0709 0.1522 1.0000
8.250 1.2955 0.02160 0.01243 -0.0701 0.1479 1.0000
8.500 1.3191 0.02204 0.01297 -0.0695 0.1437 1.0000
8.750 1.3415 0.02255 0.01354 -0.0688 0.1393 1.0000
9.000 1.3624 0.02315 0.01413 -0.0678 0.1353 1.0000
9.250 1.3838 0.02371 0.01476 -0.0670 0.1316 1.0000
9.500 1.4050 0.02425 0.01539 -0.0661 0.1277 1.0000
9.750 1.4246 0.02486 0.01604 -0.0650 0.1240 1.0000
10.000 1.4423 0.02559 0.01676 -0.0636 0.1206 1.0000
10.250 1.4619 0.02618 0.01749 -0.0625 0.1173 1.0000
10.500 1.4797 0.02683 0.01823 -0.0612 0.1139 1.0000
10.750 1.4954 0.02756 0.01900 -0.0595 0.1108 1.0000
11.000 1.5089 0.02842 0.01988 -0.0577 0.1080 1.0000
11.250 1.5232 0.02916 0.02076 -0.0558 0.1052 1.0000
11.500 1.5353 0.02999 0.02170 -0.0537 0.1024 1.0000
11.750 1.5459 0.03093 0.02271 -0.0515 0.0997 1.0000
12.000 1.5546 0.03205 0.02386 -0.0494 0.0974 1.0000
12.250 1.5652 0.03315 0.02508 -0.0475 0.0950 1.0000
12.500 1.5761 0.03427 0.02634 -0.0458 0.0925 1.0000
12.750 1.5854 0.03551 0.02769 -0.0442 0.0901 1.0000
13.000 1.5928 0.03693 0.02918 -0.0425 0.0879 1.0000
13.250 1.5979 0.03860 0.03089 -0.0409 0.0860 1.0000
13.500 1.6056 0.04016 0.03262 -0.0396 0.0841 1.0000
13.750 1.6126 0.04184 0.03446 -0.0383 0.0820 1.0000
14.000 1.6181 0.04370 0.03644 -0.0372 0.0800 1.0000
14.250 1.6216 0.04579 0.03863 -0.0363 0.0782 1.0000
14.500 1.6230 0.04815 0.04107 -0.0355 0.0766 1.0000
14.750 1.6236 0.05072 0.04372 -0.0348 0.0752 1.0000
15.000 1.6258 0.05322 0.04642 -0.0343 0.0737 1.0000
15.250 1.6263 0.05598 0.04935 -0.0340 0.0721 1.0000
15.500 1.6252 0.05900 0.05252 -0.0339 0.0706 1.0000
15.750 1.6226 0.06228 0.05593 -0.0341 0.0693 1.0000
16.000 1.6181 0.06589 0.05964 -0.0345 0.0680 1.0000
16.250 1.6121 0.06979 0.06362 -0.0351 0.0669 1.0000
16.500 1.6057 0.07389 0.06784 -0.0359 0.0658 1.0000
16.750 1.5989 0.07826 0.07242 -0.0370 0.0647 1.0000
17.000 1.5904 0.08297 0.07732 -0.0384 0.0636 1.0000
17.250 1.5809 0.08798 0.08250 -0.0401 0.0626 1.0000
17.500 1.5701 0.09332 0.08800 -0.0421 0.0616 1.0000
17.750 1.5583 0.09894 0.09376 -0.0444 0.0607 1.0000
18.000 1.5459 0.10478 0.09973 -0.0470 0.0598 1.0000
18.250 1.5344 0.11053 0.10557 -0.0496 0.0590 1.0000
18.500 1.5254 0.11578 0.11087 -0.0520 0.0581 1.0000
18.750 1.5094 0.12270 0.11797 -0.0556 0.0573 1.0000
19.000 1.4885 0.13082 0.12630 -0.0601 0.0565 1.0000
19.250 1.4649 0.13975 0.13544 -0.0654 0.0556 1.0000
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