ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 50,000 Max Cl/Cd: 36.73 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad10-il-50000-n5.txt Download as CSV file: xf-arad10-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3752 0.11311 0.10586 -0.0216 1.0000 0.1095
-8.500 -0.3740 0.10991 0.10273 -0.0227 1.0000 0.1096
-8.250 -0.3755 0.10202 0.09481 -0.0260 1.0000 0.0727
-8.000 -0.3699 0.09870 0.09154 -0.0257 1.0000 0.0714
-7.750 -0.3694 0.09541 0.08834 -0.0264 1.0000 0.0704
-7.500 -0.3685 0.09192 0.08492 -0.0278 1.0000 0.0695
-7.250 -0.3677 0.08829 0.08136 -0.0296 1.0000 0.0686
-7.000 -0.3667 0.08444 0.07756 -0.0316 1.0000 0.0676
-6.500 -0.3621 0.07350 0.06654 -0.0406 1.0000 0.0635
-6.250 -0.3539 0.06967 0.06269 -0.0418 1.0000 0.0632
-6.000 -0.3440 0.06551 0.05846 -0.0435 1.0000 0.0630
-5.750 -0.3312 0.06062 0.05340 -0.0462 1.0000 0.0632
-5.500 -0.3165 0.05632 0.04894 -0.0482 1.0000 0.0645
-5.250 -0.3029 0.05457 0.04719 -0.0475 1.0000 0.0665
-5.000 -0.2852 0.05099 0.04340 -0.0489 1.0000 0.0683
-4.750 -0.2642 0.04675 0.03879 -0.0509 1.0000 0.0698
-4.500 -0.2370 0.04117 0.03239 -0.0542 1.0000 0.0735
-4.250 -0.2202 0.04041 0.03173 -0.0532 1.0000 0.0762
-4.000 -0.1980 0.03827 0.02927 -0.0536 1.0000 0.0800
-3.750 -0.1720 0.03557 0.02597 -0.0545 1.0000 0.0855
-3.500 -0.1443 0.03453 0.02486 -0.0555 0.9974 0.0907
-3.250 -0.1020 0.03247 0.02228 -0.0589 0.9912 0.0991
-3.000 -0.0604 0.03117 0.02064 -0.0620 0.9844 0.1088
-2.750 -0.0211 0.03015 0.01950 -0.0646 0.9764 0.1182
-2.500 0.0214 0.02908 0.01815 -0.0677 0.9696 0.1295
-2.250 0.0602 0.02827 0.01706 -0.0698 0.9604 0.1421
-2.000 0.0995 0.02759 0.01635 -0.0722 0.9521 0.1554
-1.750 0.1396 0.02698 0.01565 -0.0745 0.9433 0.1711
-1.500 0.1782 0.02647 0.01506 -0.0766 0.9336 0.1892
-1.250 0.2211 0.02591 0.01445 -0.0793 0.9256 0.2112
-1.000 0.2576 0.02542 0.01403 -0.0810 0.9146 0.2346
-0.750 0.2991 0.02481 0.01352 -0.0835 0.9061 0.2665
-0.500 0.3340 0.02425 0.01317 -0.0847 0.8939 0.3089
-0.250 0.3671 0.02326 0.01293 -0.0858 0.8819 0.4282
0.000 0.3968 0.02177 0.01252 -0.0846 0.8680 1.0000
0.250 0.4324 0.02171 0.01216 -0.0853 0.8533 1.0000
0.500 0.4656 0.02161 0.01183 -0.0854 0.8360 1.0000
0.750 0.4969 0.02150 0.01153 -0.0851 0.8172 1.0000
1.000 0.5271 0.02141 0.01127 -0.0846 0.7978 1.0000
1.250 0.5566 0.02135 0.01106 -0.0839 0.7785 1.0000
1.500 0.5855 0.02131 0.01087 -0.0832 0.7590 1.0000
1.750 0.6141 0.02128 0.01070 -0.0824 0.7392 1.0000
2.000 0.6400 0.02138 0.01070 -0.0813 0.7164 1.0000
2.250 0.6667 0.02146 0.01065 -0.0802 0.6936 1.0000
2.500 0.6936 0.02153 0.01059 -0.0792 0.6704 1.0000
2.750 0.7191 0.02171 0.01066 -0.0781 0.6442 1.0000
3.000 0.7450 0.02188 0.01069 -0.0771 0.6180 1.0000
3.250 0.7702 0.02212 0.01081 -0.0760 0.5896 1.0000
3.500 0.7948 0.02241 0.01097 -0.0749 0.5592 1.0000
3.750 0.8192 0.02275 0.01116 -0.0738 0.5280 1.0000
4.000 0.8431 0.02316 0.01140 -0.0727 0.4957 1.0000
4.250 0.8666 0.02366 0.01171 -0.0716 0.4635 1.0000
4.500 0.8899 0.02423 0.01209 -0.0706 0.4333 1.0000
4.750 0.9129 0.02488 0.01254 -0.0696 0.4053 1.0000
5.000 0.9359 0.02558 0.01311 -0.0688 0.3802 1.0000
5.250 0.9591 0.02632 0.01371 -0.0680 0.3589 1.0000
5.500 0.9823 0.02710 0.01435 -0.0672 0.3403 1.0000
5.750 1.0056 0.02790 0.01506 -0.0666 0.3239 1.0000
6.000 1.0293 0.02873 0.01583 -0.0660 0.3093 1.0000
6.250 1.0528 0.02958 0.01664 -0.0654 0.2963 1.0000
6.500 1.0764 0.03046 0.01746 -0.0648 0.2847 1.0000
6.750 1.1001 0.03136 0.01833 -0.0642 0.2742 1.0000
7.000 1.1234 0.03230 0.01934 -0.0637 0.2639 1.0000
7.250 1.1471 0.03325 0.02020 -0.0631 0.2552 1.0000
7.500 1.1696 0.03427 0.02139 -0.0625 0.2460 1.0000
7.750 1.1931 0.03528 0.02235 -0.0620 0.2386 1.0000
8.000 1.2143 0.03639 0.02364 -0.0612 0.2303 1.0000
8.250 1.2380 0.03743 0.02459 -0.0608 0.2238 1.0000
8.500 1.2573 0.03873 0.02619 -0.0599 0.2164 1.0000
8.750 1.2790 0.03984 0.02731 -0.0592 0.2102 1.0000
9.000 1.2981 0.04123 0.02890 -0.0583 0.2040 1.0000
9.250 1.3165 0.04262 0.03047 -0.0573 0.1980 1.0000
9.500 1.3389 0.04376 0.03154 -0.0568 0.1930 1.0000
9.750 1.3511 0.04559 0.03375 -0.0552 0.1872 1.0000
10.000 1.3665 0.04712 0.03547 -0.0540 0.1820 1.0000
10.250 1.3879 0.04834 0.03664 -0.0534 0.1778 1.0000
10.500 1.3932 0.05064 0.03937 -0.0512 0.1731 1.0000
10.750 1.4011 0.05265 0.04163 -0.0494 0.1685 1.0000
11.000 1.4161 0.05409 0.04315 -0.0482 0.1645 1.0000
11.250 1.4254 0.05613 0.04534 -0.0466 0.1611 1.0000
11.500 1.4150 0.05927 0.04891 -0.0434 0.1578 1.0000
11.750 1.4053 0.06210 0.05202 -0.0403 0.1548 1.0000
12.000 1.4020 0.06451 0.05460 -0.0380 0.1519 1.0000
12.250 1.4181 0.06578 0.05584 -0.0370 0.1487 1.0000
12.500 1.3968 0.06987 0.06021 -0.0345 0.1470 1.0000
12.750 1.3539 0.07645 0.06717 -0.0330 0.1458 1.0000
13.000 1.2891 0.08715 0.07824 -0.0352 0.1453 1.0000
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Polar data table (+)
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