ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 100,000 Max Cl/Cd: 66.55 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad6-il-100000-n5.txt Download as CSV file: xf-arad6-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3468 0.10250 0.09759 -0.0249 1.0000 0.0435
-7.500 -0.3525 0.10076 0.09592 -0.0231 1.0000 0.0441
-7.250 -0.3579 0.09898 0.09422 -0.0215 1.0000 0.0448
-7.000 -0.3604 0.09690 0.09221 -0.0207 1.0000 0.0456
-6.750 -0.3618 0.09474 0.09011 -0.0205 1.0000 0.0465
-6.500 -0.3616 0.09250 0.08792 -0.0209 1.0000 0.0475
-6.250 -0.3586 0.09020 0.08567 -0.0227 1.0000 0.0489
-6.000 -0.3461 0.08798 0.08345 -0.0298 1.0000 0.0503
-5.750 -0.2995 0.08315 0.07847 -0.0449 0.9957 0.0509
-5.500 -0.2972 0.07808 0.07351 -0.0402 0.9933 0.0524
-5.250 -0.2757 0.07438 0.06979 -0.0422 0.9895 0.0542
-5.000 -0.2430 0.07012 0.06547 -0.0487 0.9859 0.0556
-4.500 -0.1510 0.05737 0.05231 -0.0699 0.9780 0.0375
-4.250 -0.1116 0.05276 0.04757 -0.0766 0.9750 0.0354
-4.000 -0.0613 0.04708 0.04164 -0.0859 0.9729 0.0334
-3.750 -0.0155 0.04194 0.03621 -0.0933 0.9688 0.0330
-3.500 0.0313 0.03747 0.03139 -0.0999 0.9657 0.0349
-3.250 0.0818 0.03208 0.02545 -0.1067 0.9637 0.0350
-3.000 0.1305 0.02737 0.01995 -0.1122 0.9623 0.0351
-2.750 0.1746 0.02430 0.01614 -0.1160 0.9608 0.0362
-2.500 0.2161 0.02231 0.01358 -0.1188 0.9592 0.0381
-2.250 0.2477 0.02135 0.01246 -0.1198 0.9534 0.0422
-2.000 0.2842 0.02053 0.01143 -0.1216 0.9496 0.0488
-1.750 0.3229 0.01962 0.01043 -0.1238 0.9469 0.0575
-1.500 0.3581 0.01916 0.00991 -0.1254 0.9426 0.0777
-1.250 0.3905 0.01894 0.00974 -0.1264 0.9365 0.1019
-1.000 0.4282 0.01856 0.00936 -0.1285 0.9329 0.1248
-0.750 0.4620 0.01824 0.00904 -0.1297 0.9277 0.1454
-0.500 0.4942 0.01800 0.00882 -0.1305 0.9213 0.1703
-0.250 0.5312 0.01768 0.00854 -0.1323 0.9174 0.2004
0.000 0.5603 0.01751 0.00844 -0.1325 0.9093 0.2342
0.250 0.5958 0.01713 0.00825 -0.1340 0.9043 0.2922
0.500 0.6174 0.01560 0.00817 -0.1325 0.8959 1.0000
0.750 0.6512 0.01555 0.00795 -0.1334 0.8897 1.0000
1.000 0.6800 0.01562 0.00792 -0.1334 0.8806 1.0000
1.250 0.7140 0.01552 0.00773 -0.1342 0.8742 1.0000
1.500 0.7432 0.01540 0.00755 -0.1339 0.8612 1.0000
1.750 0.7741 0.01509 0.00715 -0.1336 0.8448 1.0000
2.000 0.8005 0.01491 0.00692 -0.1324 0.8226 1.0000
2.250 0.8297 0.01476 0.00671 -0.1319 0.8037 1.0000
2.500 0.8582 0.01472 0.00663 -0.1315 0.7871 1.0000
2.750 0.8853 0.01477 0.00669 -0.1309 0.7685 1.0000
3.000 0.9127 0.01481 0.00670 -0.1304 0.7486 1.0000
3.250 0.9399 0.01488 0.00673 -0.1297 0.7264 1.0000
3.500 0.9667 0.01497 0.00677 -0.1290 0.7009 1.0000
3.750 0.9927 0.01513 0.00689 -0.1281 0.6704 1.0000
4.000 1.0179 0.01535 0.00702 -0.1271 0.6340 1.0000
4.250 1.0422 0.01566 0.00718 -0.1260 0.5891 1.0000
4.500 1.0650 0.01611 0.00740 -0.1246 0.5327 1.0000
4.750 1.0855 0.01679 0.00776 -0.1229 0.4615 1.0000
5.000 1.1040 0.01771 0.00825 -0.1211 0.3850 1.0000
5.250 1.1224 0.01871 0.00887 -0.1195 0.3242 1.0000
5.500 1.1420 0.01963 0.00955 -0.1182 0.2831 1.0000
5.750 1.1624 0.02047 0.01026 -0.1170 0.2544 1.0000
6.000 1.1830 0.02128 0.01101 -0.1159 0.2316 1.0000
6.250 1.2038 0.02205 0.01175 -0.1148 0.2126 1.0000
6.500 1.2244 0.02282 0.01251 -0.1136 0.1960 1.0000
6.750 1.2449 0.02360 0.01329 -0.1124 0.1811 1.0000
7.000 1.2651 0.02438 0.01413 -0.1113 0.1673 1.0000
7.250 1.2852 0.02518 0.01497 -0.1100 0.1547 1.0000
7.500 1.3048 0.02601 0.01586 -0.1088 0.1431 1.0000
7.750 1.3237 0.02688 0.01676 -0.1074 0.1319 1.0000
8.000 1.3417 0.02780 0.01770 -0.1060 0.1216 1.0000
8.250 1.3605 0.02868 0.01875 -0.1046 0.1116 1.0000
8.500 1.3781 0.02965 0.01982 -0.1030 0.1025 1.0000
8.750 1.3936 0.03075 0.02092 -0.1013 0.0951 1.0000
9.000 1.4107 0.03182 0.02220 -0.0996 0.0878 1.0000
9.250 1.4243 0.03307 0.02347 -0.0976 0.0819 1.0000
9.500 1.4396 0.03421 0.02483 -0.0958 0.0752 1.0000
9.750 1.4505 0.03561 0.02629 -0.0935 0.0706 1.0000
10.000 1.4644 0.03698 0.02793 -0.0914 0.0654 1.0000
10.250 1.4732 0.03828 0.02935 -0.0888 0.0607 1.0000
10.500 1.4807 0.03982 0.03105 -0.0861 0.0561 1.0000
10.750 1.4874 0.04109 0.03250 -0.0835 0.0506 1.0000
11.000 1.4920 0.04266 0.03421 -0.0809 0.0456 1.0000
11.250 1.4975 0.04425 0.03601 -0.0785 0.0408 1.0000
11.500 1.4970 0.04640 0.03820 -0.0758 0.0377 1.0000
11.750 1.5005 0.04865 0.04085 -0.0734 0.0342 1.0000
12.000 1.5002 0.05101 0.04341 -0.0711 0.0312 1.0000
12.250 1.4955 0.05378 0.04628 -0.0690 0.0290 1.0000
12.500 1.4915 0.05693 0.04970 -0.0670 0.0268 1.0000
12.750 1.4864 0.06024 0.05330 -0.0654 0.0249 1.0000
13.000 1.4791 0.06386 0.05713 -0.0642 0.0235 1.0000
13.250 1.4700 0.06784 0.06131 -0.0634 0.0226 1.0000
13.500 1.4590 0.07226 0.06592 -0.0632 0.0219 1.0000
13.750 1.4458 0.07722 0.07106 -0.0635 0.0214 1.0000
14.000 1.4312 0.08270 0.07672 -0.0644 0.0210 1.0000
14.250 1.4156 0.08879 0.08304 -0.0659 0.0207 1.0000
14.500 1.3988 0.09550 0.09002 -0.0684 0.0205 1.0000
14.750 1.3807 0.10299 0.09776 -0.0717 0.0204 1.0000
15.000 1.3619 0.11120 0.10620 -0.0761 0.0204 1.0000
15.250 1.3423 0.12015 0.11535 -0.0812 0.0204 1.0000
15.500 1.3223 0.12983 0.12521 -0.0872 0.0205 1.0000
15.750 1.3022 0.14015 0.13569 -0.0936 0.0207 1.0000
16.000 1.2824 0.15093 0.14659 -0.1004 0.0209 1.0000
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Polar data table (+)
Polar graphs
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