ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 50,000 Max Cl/Cd: 25.73 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad13-il-50000.txt Download as CSV file: xf-arad13-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4216 0.12470 0.11780 -0.0056 1.0000 0.2171
-9.000 -0.3725 0.11629 0.10934 -0.0020 1.0000 0.2247
-8.750 -0.3789 0.11428 0.10741 -0.0037 1.0000 0.2338
-8.500 -0.3769 0.11042 0.10364 -0.0045 1.0000 0.2391
-8.250 -0.3639 0.10704 0.10029 -0.0040 1.0000 0.2509
-8.000 -0.3711 0.10402 0.09738 -0.0053 1.0000 0.2581
-7.750 -0.3621 0.10100 0.09442 -0.0048 1.0000 0.2714
-7.500 -0.3540 0.09709 0.09059 -0.0045 1.0000 0.2805
-7.250 -0.3771 0.09597 0.08962 -0.0054 1.0000 0.2929
-7.000 -0.3477 0.09113 0.08479 -0.0035 1.0000 0.3065
-6.750 -0.3475 0.08814 0.08192 -0.0025 1.0000 0.3213
-6.500 -0.3502 0.08543 0.07933 -0.0017 1.0000 0.3386
-6.250 -0.3466 0.08266 0.07665 0.0000 1.0000 0.3587
-6.000 -0.3421 0.07997 0.07408 0.0022 1.0000 0.3799
-5.750 -0.3402 0.07774 0.07196 0.0052 1.0000 0.4054
-5.250 -0.3442 0.07408 0.06856 0.0142 1.0000 0.4671
-5.000 -0.3380 0.07208 0.06666 0.0197 1.0000 0.5046
-4.750 -0.2993 0.06924 0.06382 0.0252 1.0000 0.5816
-4.500 -0.3327 0.04966 0.04216 -0.0304 1.0000 0.1972
-4.250 -0.3176 0.04687 0.03914 -0.0306 1.0000 0.1966
-4.000 -0.2995 0.04432 0.03622 -0.0312 1.0000 0.1969
-3.750 -0.2804 0.04207 0.03363 -0.0317 1.0000 0.1997
-3.500 -0.2636 0.04061 0.03216 -0.0313 1.0000 0.2046
-3.250 -0.2420 0.03927 0.03054 -0.0318 1.0000 0.2107
-3.000 -0.2171 0.03812 0.02880 -0.0328 1.0000 0.2170
-2.750 -0.1980 0.03708 0.02788 -0.0329 1.0000 0.2248
-2.500 -0.1418 0.03554 0.02597 -0.0390 0.9888 0.2405
-2.250 -0.0852 0.03430 0.02452 -0.0450 0.9758 0.2602
-2.000 -0.0307 0.03327 0.02340 -0.0504 0.9619 0.2844
-1.750 0.0235 0.03237 0.02240 -0.0554 0.9472 0.3149
-1.500 0.0786 0.03146 0.02159 -0.0602 0.9323 0.3548
-1.250 0.1398 0.03019 0.02071 -0.0658 0.9185 0.4200
-1.000 0.1888 0.02732 0.02025 -0.0667 0.9034 1.0000
-0.750 0.2488 0.02739 0.01939 -0.0719 0.8852 1.0000
-0.500 0.2968 0.02740 0.01903 -0.0748 0.8664 1.0000
-0.250 0.3390 0.02743 0.01879 -0.0765 0.8472 1.0000
0.000 0.3762 0.02747 0.01862 -0.0772 0.8278 1.0000
0.250 0.4096 0.02754 0.01850 -0.0769 0.8082 1.0000
0.500 0.4401 0.02763 0.01842 -0.0761 0.7884 1.0000
0.750 0.4685 0.02773 0.01837 -0.0748 0.7686 1.0000
1.000 0.4957 0.02782 0.01831 -0.0732 0.7486 1.0000
1.250 0.5221 0.02792 0.01826 -0.0715 0.7286 1.0000
1.500 0.5475 0.02805 0.01824 -0.0696 0.7082 1.0000
1.750 0.5709 0.02840 0.01849 -0.0679 0.6856 1.0000
2.000 0.5954 0.02865 0.01862 -0.0662 0.6637 1.0000
2.250 0.6204 0.02888 0.01872 -0.0645 0.6422 1.0000
2.500 0.6456 0.02909 0.01879 -0.0628 0.6210 1.0000
2.750 0.6712 0.02932 0.01888 -0.0612 0.6004 1.0000
3.000 0.6968 0.02961 0.01902 -0.0598 0.5802 1.0000
3.250 0.7225 0.02994 0.01920 -0.0585 0.5605 1.0000
3.500 0.7481 0.03038 0.01952 -0.0573 0.5414 1.0000
3.750 0.7736 0.03092 0.01994 -0.0563 0.5228 1.0000
4.000 0.7987 0.03156 0.02049 -0.0554 0.5049 1.0000
4.250 0.8233 0.03236 0.02124 -0.0547 0.4878 1.0000
4.500 0.8476 0.03327 0.02211 -0.0540 0.4717 1.0000
4.750 0.8718 0.03422 0.02302 -0.0533 0.4569 1.0000
5.000 0.8975 0.03503 0.02373 -0.0527 0.4442 1.0000
5.250 0.9229 0.03587 0.02450 -0.0520 0.4314 1.0000
5.500 0.9433 0.03745 0.02619 -0.0516 0.4183 1.0000
5.750 0.9673 0.03860 0.02733 -0.0510 0.4079 1.0000
6.000 0.9902 0.03986 0.02861 -0.0505 0.3971 1.0000
6.250 1.0071 0.04192 0.03082 -0.0499 0.3869 1.0000
6.500 1.0336 0.04279 0.03159 -0.0493 0.3781 1.0000
6.750 1.0428 0.04581 0.03491 -0.0486 0.3691 1.0000
7.000 1.0685 0.04677 0.03581 -0.0480 0.3610 1.0000
7.250 1.0726 0.05032 0.03963 -0.0471 0.3534 1.0000
7.500 1.0768 0.05371 0.04323 -0.0462 0.3463 1.0000
7.750 1.1103 0.05403 0.04342 -0.0457 0.3398 1.0000
8.000 1.0363 0.06584 0.05583 -0.0440 0.3360 1.0000
8.250 0.8513 0.09513 0.08533 -0.0536 0.3435 1.0000
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Polar data table (+)
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