ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 100,000 Max Cl/Cd: 44.54 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad13-il-100000-n5.txt Download as CSV file: xf-arad13-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4538 0.09191 0.08675 -0.0189 1.0000 0.0411
-9.000 -0.4643 0.08564 0.08053 -0.0227 1.0000 0.0410
-8.750 -0.4839 0.07827 0.07323 -0.0280 1.0000 0.0409
-8.500 -0.5108 0.06609 0.06094 -0.0379 1.0000 0.0407
-8.250 -0.5538 0.04634 0.04027 -0.0475 1.0000 0.0416
-8.000 -0.5535 0.03785 0.03075 -0.0493 1.0000 0.0439
-7.750 -0.5311 0.03702 0.02993 -0.0490 1.0000 0.0452
-7.500 -0.5122 0.03434 0.02688 -0.0490 1.0000 0.0472
-7.250 -0.4929 0.03146 0.02352 -0.0487 1.0000 0.0493
-7.000 -0.4712 0.03071 0.02278 -0.0481 1.0000 0.0511
-6.750 -0.4518 0.02893 0.02063 -0.0472 1.0000 0.0540
-6.500 -0.4333 0.02813 0.01982 -0.0460 1.0000 0.0559
-6.250 -0.4000 0.02698 0.01848 -0.0477 0.9934 0.0594
-6.000 -0.3616 0.02588 0.01724 -0.0502 0.9836 0.0630
-5.750 -0.3238 0.02467 0.01571 -0.0523 0.9724 0.0678
-5.500 -0.2867 0.02401 0.01511 -0.0544 0.9601 0.0715
-5.250 -0.2500 0.02308 0.01399 -0.0561 0.9473 0.0766
-5.000 -0.2144 0.02248 0.01336 -0.0576 0.9337 0.0814
-4.750 -0.1803 0.02181 0.01260 -0.0587 0.9192 0.0867
-4.500 -0.1488 0.02129 0.01198 -0.0591 0.9028 0.0925
-4.250 -0.1190 0.02081 0.01148 -0.0592 0.8863 0.0980
-4.000 -0.0900 0.02037 0.01091 -0.0589 0.8699 0.1049
-3.750 -0.0621 0.02000 0.01057 -0.0586 0.8538 0.1111
-3.500 -0.0343 0.01962 0.01009 -0.0581 0.8382 0.1188
-3.250 -0.0070 0.01932 0.00977 -0.0575 0.8231 0.1267
-3.000 0.0203 0.01900 0.00942 -0.0570 0.8074 0.1354
-2.750 0.0480 0.01875 0.00910 -0.0566 0.7916 0.1457
-2.500 0.0753 0.01847 0.00884 -0.0561 0.7761 0.1561
-2.250 0.1026 0.01822 0.00856 -0.0556 0.7607 0.1680
-2.000 0.1301 0.01802 0.00830 -0.0551 0.7450 0.1816
-1.750 0.1575 0.01780 0.00806 -0.0546 0.7288 0.1966
-1.500 0.1851 0.01757 0.00785 -0.0542 0.7120 0.2138
-1.250 0.2129 0.01736 0.00765 -0.0538 0.6957 0.2347
-1.000 0.2406 0.01711 0.00747 -0.0535 0.6799 0.2625
-0.750 0.2680 0.01681 0.00731 -0.0532 0.6644 0.3109
-0.500 0.2936 0.01605 0.00720 -0.0527 0.6495 0.4866
-0.250 0.3111 0.01491 0.00720 -0.0487 0.6348 0.8664
0.000 0.3536 0.01475 0.00692 -0.0511 0.6166 1.0000
0.250 0.3812 0.01487 0.00684 -0.0508 0.6002 1.0000
0.500 0.4088 0.01501 0.00679 -0.0505 0.5837 1.0000
0.750 0.4364 0.01516 0.00675 -0.0502 0.5670 1.0000
1.000 0.4641 0.01533 0.00674 -0.0499 0.5500 1.0000
1.250 0.4918 0.01551 0.00675 -0.0497 0.5327 1.0000
1.500 0.5194 0.01570 0.00678 -0.0495 0.5150 1.0000
1.750 0.5471 0.01591 0.00683 -0.0493 0.4973 1.0000
2.000 0.5747 0.01613 0.00691 -0.0491 0.4792 1.0000
2.250 0.6022 0.01637 0.00701 -0.0490 0.4607 1.0000
2.500 0.6297 0.01664 0.00713 -0.0488 0.4422 1.0000
2.750 0.6570 0.01692 0.00727 -0.0486 0.4236 1.0000
3.000 0.6842 0.01723 0.00744 -0.0485 0.4052 1.0000
3.250 0.7113 0.01756 0.00764 -0.0483 0.3875 1.0000
3.500 0.7383 0.01791 0.00787 -0.0482 0.3704 1.0000
3.750 0.7650 0.01829 0.00812 -0.0480 0.3543 1.0000
4.000 0.7915 0.01869 0.00839 -0.0478 0.3395 1.0000
4.250 0.8180 0.01911 0.00870 -0.0477 0.3256 1.0000
4.500 0.8445 0.01953 0.00905 -0.0475 0.3128 1.0000
4.750 0.8706 0.01999 0.00942 -0.0473 0.3016 1.0000
5.000 0.8965 0.02046 0.00980 -0.0471 0.2911 1.0000
5.250 0.9226 0.02093 0.01023 -0.0469 0.2813 1.0000
5.500 0.9479 0.02145 0.01065 -0.0466 0.2728 1.0000
5.750 0.9738 0.02193 0.01113 -0.0464 0.2642 1.0000
6.000 0.9988 0.02248 0.01160 -0.0461 0.2568 1.0000
6.250 1.0242 0.02300 0.01212 -0.0459 0.2495 1.0000
6.500 1.0490 0.02355 0.01266 -0.0456 0.2426 1.0000
6.750 1.0734 0.02415 0.01319 -0.0452 0.2368 1.0000
7.000 1.0982 0.02471 0.01381 -0.0449 0.2303 1.0000
7.250 1.1221 0.02531 0.01438 -0.0445 0.2248 1.0000
7.500 1.1459 0.02595 0.01501 -0.0441 0.2197 1.0000
7.750 1.1696 0.02657 0.01571 -0.0437 0.2141 1.0000
8.000 1.1926 0.02721 0.01634 -0.0432 0.2093 1.0000
8.250 1.2154 0.02792 0.01702 -0.0426 0.2050 1.0000
8.500 1.2379 0.02861 0.01784 -0.0421 0.2000 1.0000
8.750 1.2597 0.02931 0.01857 -0.0415 0.1956 1.0000
9.000 1.2812 0.03005 0.01927 -0.0408 0.1919 1.0000
9.250 1.3021 0.03086 0.02019 -0.0401 0.1878 1.0000
9.500 1.3222 0.03166 0.02110 -0.0393 0.1836 1.0000
9.750 1.3419 0.03245 0.02193 -0.0385 0.1799 1.0000
10.000 1.3614 0.03328 0.02273 -0.0377 0.1768 1.0000
10.250 1.3791 0.03424 0.02385 -0.0367 0.1733 1.0000
10.500 1.3956 0.03521 0.02495 -0.0355 0.1696 1.0000
10.750 1.4116 0.03614 0.02595 -0.0343 0.1664 1.0000
11.000 1.4276 0.03706 0.02689 -0.0331 0.1636 1.0000
11.250 1.4421 0.03814 0.02803 -0.0318 0.1610 1.0000
11.500 1.4516 0.03940 0.02950 -0.0300 0.1579 1.0000
11.750 1.4595 0.04062 0.03087 -0.0279 0.1550 1.0000
12.000 1.4674 0.04184 0.03217 -0.0259 0.1525 1.0000
12.250 1.4770 0.04304 0.03341 -0.0243 0.1503 1.0000
12.500 1.4873 0.04437 0.03474 -0.0230 0.1482 1.0000
12.750 1.4865 0.04642 0.03707 -0.0210 0.1458 1.0000
13.000 1.4871 0.04850 0.03937 -0.0196 0.1433 1.0000
13.250 1.4891 0.05056 0.04157 -0.0184 0.1410 1.0000
13.500 1.4931 0.05250 0.04360 -0.0176 0.1389 1.0000
13.750 1.5001 0.05425 0.04538 -0.0168 0.1371 1.0000
14.000 1.5043 0.05636 0.04757 -0.0162 0.1353 1.0000
14.250 1.4908 0.06034 0.05186 -0.0160 0.1334 1.0000
14.500 1.4775 0.06455 0.05633 -0.0162 0.1314 1.0000
14.750 1.4648 0.06890 0.06089 -0.0168 0.1296 1.0000
15.000 1.4548 0.07307 0.06523 -0.0176 0.1278 1.0000
15.250 1.4506 0.07659 0.06883 -0.0183 0.1261 1.0000
15.500 1.4567 0.07875 0.07100 -0.0184 0.1246 1.0000
15.750 1.4365 0.08471 0.07715 -0.0204 0.1231 1.0000
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