ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 50,000 Max Cl/Cd: 45.77 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad6-il-50000-n5.txt Download as CSV file: xf-arad6-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 6% 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3490 0.10786 0.10094 -0.0251 1.0000 0.0867
-7.500 -0.3544 0.10634 0.09953 -0.0244 1.0000 0.0885
-7.250 -0.3587 0.10522 0.09852 -0.0258 1.0000 0.0902
-7.000 -0.3602 0.10413 0.09752 -0.0289 1.0000 0.0910
-6.750 -0.3561 0.10250 0.09594 -0.0331 1.0000 0.0914
-6.500 -0.3523 0.09743 0.09096 -0.0285 1.0000 0.0924
-6.250 -0.3477 0.09392 0.08749 -0.0263 1.0000 0.0940
-6.000 -0.3427 0.09105 0.08467 -0.0258 1.0000 0.0958
-5.750 -0.3364 0.08833 0.08199 -0.0263 1.0000 0.0980
-5.500 -0.3277 0.08562 0.07930 -0.0282 1.0000 0.1009
-5.250 -0.3041 0.08337 0.07696 -0.0379 1.0000 0.1053
-5.000 -0.2846 0.07993 0.07350 -0.0426 1.0000 0.1060
-4.750 -0.2833 0.07620 0.06987 -0.0382 1.0000 0.1079
-4.500 -0.2728 0.07332 0.06699 -0.0375 1.0000 0.1121
-3.750 -0.1657 0.05800 0.05101 -0.0593 1.0000 0.0624
-3.500 -0.1396 0.05458 0.04749 -0.0621 1.0000 0.0602
-3.250 -0.1051 0.05075 0.04345 -0.0669 1.0000 0.0581
-3.000 -0.0660 0.04675 0.03915 -0.0723 1.0000 0.0564
-2.750 -0.0255 0.04296 0.03499 -0.0773 1.0000 0.0558
-2.500 0.0128 0.04000 0.03161 -0.0813 1.0000 0.0585
-2.250 0.0616 0.03650 0.02743 -0.0869 0.9985 0.0617
-2.000 0.1114 0.03325 0.02336 -0.0919 0.9965 0.0635
-1.750 0.1528 0.03153 0.02133 -0.0953 0.9932 0.0679
-1.500 0.1949 0.03008 0.01932 -0.0984 0.9893 0.0786
-1.250 0.2359 0.02914 0.01811 -0.1013 0.9856 0.0931
-1.000 0.2730 0.02858 0.01738 -0.1034 0.9801 0.1141
-0.750 0.3122 0.02805 0.01659 -0.1057 0.9754 0.1400
-0.500 0.3498 0.02760 0.01593 -0.1077 0.9701 0.1661
-0.250 0.3860 0.02729 0.01558 -0.1096 0.9639 0.1970
0.000 0.4263 0.02699 0.01528 -0.1124 0.9592 0.2380
0.250 0.4591 0.02670 0.01516 -0.1138 0.9511 0.2860
0.500 0.4997 0.02591 0.01512 -0.1169 0.9466 0.4393
0.750 0.5226 0.02509 0.01492 -0.1157 0.9354 1.0000
1.000 0.5578 0.02540 0.01494 -0.1173 0.9273 1.0000
1.250 0.5929 0.02568 0.01503 -0.1189 0.9188 1.0000
1.500 0.6237 0.02599 0.01523 -0.1197 0.9087 1.0000
1.750 0.6609 0.02619 0.01534 -0.1216 0.9008 1.0000
2.000 0.6927 0.02644 0.01555 -0.1225 0.8904 1.0000
2.250 0.7233 0.02669 0.01578 -0.1230 0.8793 1.0000
2.500 0.7582 0.02671 0.01583 -0.1241 0.8673 1.0000
2.750 0.7963 0.02627 0.01541 -0.1250 0.8508 1.0000
3.000 0.8358 0.02552 0.01470 -0.1255 0.8324 1.0000
3.250 0.8673 0.02506 0.01433 -0.1249 0.8122 1.0000
3.500 0.8974 0.02478 0.01412 -0.1242 0.7935 1.0000
3.750 0.9291 0.02442 0.01385 -0.1237 0.7748 1.0000
4.000 0.9562 0.02426 0.01379 -0.1226 0.7527 1.0000
4.250 0.9866 0.02393 0.01358 -0.1218 0.7295 1.0000
4.500 1.0134 0.02377 0.01350 -0.1204 0.7007 1.0000
4.750 1.0383 0.02372 0.01353 -0.1188 0.6657 1.0000
5.000 1.0640 0.02368 0.01352 -0.1171 0.6233 1.0000
5.250 1.0883 0.02379 0.01352 -0.1152 0.5688 1.0000
5.500 1.1094 0.02424 0.01371 -0.1130 0.5003 1.0000
5.750 1.1270 0.02511 0.01417 -0.1105 0.4272 1.0000
6.000 1.1424 0.02631 0.01496 -0.1082 0.3673 1.0000
6.250 1.1582 0.02760 0.01600 -0.1062 0.3240 1.0000
6.500 1.1754 0.02889 0.01710 -0.1045 0.2923 1.0000
6.750 1.1938 0.03015 0.01827 -0.1031 0.2665 1.0000
7.000 1.2134 0.03138 0.01948 -0.1019 0.2447 1.0000
7.250 1.2335 0.03260 0.02071 -0.1008 0.2249 1.0000
7.500 1.2539 0.03385 0.02202 -0.0997 0.2078 1.0000
7.750 1.2741 0.03513 0.02330 -0.0986 0.1920 1.0000
8.000 1.2945 0.03643 0.02469 -0.0975 0.1774 1.0000
8.250 1.3139 0.03776 0.02612 -0.0963 0.1637 1.0000
8.500 1.3344 0.03919 0.02779 -0.0953 0.1514 1.0000
8.750 1.3531 0.04069 0.02949 -0.0940 0.1396 1.0000
9.000 1.3707 0.04227 0.03125 -0.0926 0.1289 1.0000
9.250 1.3891 0.04396 0.03303 -0.0914 0.1206 1.0000
9.500 1.4040 0.04569 0.03505 -0.0897 0.1115 1.0000
9.750 1.4184 0.04767 0.03729 -0.0880 0.1036 1.0000
10.000 1.4333 0.04968 0.03952 -0.0864 0.0974 1.0000
10.250 1.4440 0.05214 0.04235 -0.0844 0.0910 1.0000
10.500 1.4513 0.05412 0.04453 -0.0820 0.0851 1.0000
10.750 1.4590 0.05688 0.04756 -0.0798 0.0807 1.0000
11.000 1.4577 0.05991 0.05106 -0.0766 0.0761 1.0000
11.250 1.4570 0.06185 0.05309 -0.0736 0.0720 1.0000
11.500 1.4518 0.06486 0.05635 -0.0705 0.0689 1.0000
11.750 1.4375 0.06886 0.06084 -0.0671 0.0666 1.0000
12.000 1.4225 0.07284 0.06517 -0.0645 0.0643 1.0000
12.250 1.4101 0.07648 0.06904 -0.0626 0.0620 1.0000
12.500 1.4108 0.07851 0.07093 -0.0613 0.0585 1.0000
12.750 1.3870 0.08414 0.07696 -0.0605 0.0579 1.0000
13.000 1.3623 0.09041 0.08356 -0.0610 0.0576 1.0000
13.250 1.3368 0.09741 0.09083 -0.0628 0.0577 1.0000
13.500 1.3109 0.10522 0.09885 -0.0659 0.0580 1.0000
13.750 1.2854 0.11386 0.10766 -0.0703 0.0584 1.0000
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Polar data table (+)
Polar graphs
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