ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 50,000 Max Cl/Cd: 34.72 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad10-il-50000.txt Download as CSV file: xf-arad10-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3525 0.10890 0.10186 -0.0159 1.0000 0.1855
-8.000 -0.3652 0.10793 0.10102 -0.0175 1.0000 0.1912
-7.750 -0.3851 0.10719 0.10046 -0.0204 1.0000 0.1931
-7.500 -0.3493 0.10054 0.09374 -0.0162 1.0000 0.2030
-7.250 -0.3688 0.09998 0.09335 -0.0186 1.0000 0.2087
-7.000 -0.3565 0.09540 0.08883 -0.0164 1.0000 0.2141
-6.750 -0.3557 0.09297 0.08649 -0.0162 1.0000 0.2229
-6.500 -0.3634 0.09059 0.08423 -0.0181 1.0000 0.2286
-6.250 -0.3533 0.08721 0.08091 -0.0151 1.0000 0.2368
-6.000 -0.3605 0.08503 0.07882 -0.0176 1.0000 0.2455
-5.750 -0.3530 0.08195 0.07581 -0.0145 1.0000 0.2547
-5.500 -0.3533 0.07920 0.07314 -0.0146 1.0000 0.2648
-5.250 -0.3526 0.07682 0.07082 -0.0154 1.0000 0.2795
-5.000 -0.3493 0.07429 0.06833 -0.0144 1.0000 0.2963
-4.750 -0.3456 0.07161 0.06573 -0.0120 1.0000 0.3143
-4.500 -0.3419 0.06901 0.06321 -0.0089 1.0000 0.3338
-4.250 -0.3380 0.06678 0.06105 -0.0067 1.0000 0.3595
-4.000 -0.3355 0.06424 0.05861 -0.0033 1.0000 0.3868
-3.750 -0.3345 0.06207 0.05653 0.0013 1.0000 0.4227
-3.500 -0.3379 0.06014 0.05473 0.0079 1.0000 0.4722
-3.250 -0.1899 0.04809 0.04069 -0.0429 1.0000 0.2270
-2.750 -0.1267 0.04059 0.03235 -0.0482 1.0000 0.1969
-2.500 -0.0977 0.03836 0.02976 -0.0497 1.0000 0.1986
-2.250 -0.0686 0.03669 0.02770 -0.0509 1.0000 0.2050
-2.000 -0.0394 0.03519 0.02579 -0.0521 1.0000 0.2124
-1.750 -0.0135 0.03420 0.02459 -0.0527 1.0000 0.2219
-1.500 0.0120 0.03334 0.02356 -0.0532 1.0000 0.2334
-1.250 0.0376 0.03277 0.02271 -0.0538 1.0000 0.2461
-1.000 0.0621 0.03243 0.02220 -0.0542 1.0000 0.2610
-0.750 0.0854 0.03216 0.02189 -0.0544 1.0000 0.2786
-0.500 0.1086 0.03206 0.02177 -0.0546 1.0000 0.2987
-0.250 0.1325 0.03213 0.02182 -0.0550 1.0000 0.3237
0.000 0.1753 0.03200 0.02181 -0.0586 0.9944 0.3679
0.250 0.2382 0.03095 0.02172 -0.0654 0.9831 0.5041
0.500 0.2823 0.02999 0.02128 -0.0679 0.9627 1.0000
0.750 0.3436 0.03059 0.02141 -0.0744 0.9428 1.0000
1.000 0.4008 0.03093 0.02148 -0.0798 0.9218 1.0000
1.250 0.4483 0.03112 0.02152 -0.0833 0.8990 1.0000
1.500 0.5039 0.03098 0.02125 -0.0876 0.8778 1.0000
1.750 0.5659 0.03037 0.02056 -0.0924 0.8580 1.0000
2.000 0.6057 0.03012 0.02027 -0.0933 0.8341 1.0000
2.250 0.6521 0.02939 0.01951 -0.0945 0.8118 1.0000
2.500 0.6987 0.02837 0.01845 -0.0950 0.7905 1.0000
2.750 0.7293 0.02797 0.01804 -0.0935 0.7632 1.0000
3.000 0.7677 0.02698 0.01697 -0.0922 0.7392 1.0000
3.250 0.7953 0.02659 0.01652 -0.0898 0.7080 1.0000
3.500 0.8229 0.02623 0.01606 -0.0874 0.6752 1.0000
3.750 0.8497 0.02598 0.01564 -0.0850 0.6403 1.0000
4.000 0.8759 0.02594 0.01538 -0.0827 0.6043 1.0000
4.250 0.8998 0.02631 0.01555 -0.0807 0.5667 1.0000
4.500 0.9243 0.02679 0.01581 -0.0789 0.5323 1.0000
4.750 0.9499 0.02736 0.01610 -0.0776 0.5029 1.0000
5.000 0.9737 0.02822 0.01688 -0.0764 0.4747 1.0000
5.250 0.9993 0.02905 0.01749 -0.0755 0.4519 1.0000
5.500 1.0231 0.03013 0.01854 -0.0747 0.4304 1.0000
5.750 1.0477 0.03120 0.01957 -0.0740 0.4118 1.0000
6.000 1.0721 0.03237 0.02070 -0.0733 0.3953 1.0000
6.250 1.0964 0.03362 0.02193 -0.0727 0.3805 1.0000
6.500 1.1210 0.03489 0.02318 -0.0721 0.3670 1.0000
6.750 1.1465 0.03615 0.02436 -0.0716 0.3547 1.0000
7.000 1.1664 0.03787 0.02632 -0.0708 0.3426 1.0000
7.250 1.1876 0.03961 0.02817 -0.0700 0.3319 1.0000
7.500 1.2133 0.04103 0.02952 -0.0696 0.3222 1.0000
7.750 1.2270 0.04344 0.03233 -0.0683 0.3128 1.0000
8.000 1.2517 0.04503 0.03384 -0.0679 0.3041 1.0000
8.250 1.2598 0.04796 0.03727 -0.0662 0.2963 1.0000
8.500 1.2881 0.04949 0.03862 -0.0661 0.2887 1.0000
8.750 1.2831 0.05351 0.04329 -0.0636 0.2826 1.0000
9.000 1.2988 0.05582 0.04571 -0.0625 0.2756 1.0000
9.250 1.3075 0.05915 0.04923 -0.0611 0.2705 1.0000
9.500 1.2821 0.06506 0.05566 -0.0581 0.2677 1.0000
9.750 1.2378 0.07264 0.06362 -0.0551 0.2670 1.0000
10.000 1.1623 0.08347 0.07465 -0.0531 0.2699 1.0000
10.250 1.1000 0.09701 0.08824 -0.0572 0.2728 1.0000
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Polar data table (+)
Polar graphs
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