ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 100,000 Max Cl/Cd: 68.88 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad6-il-100000.txt Download as CSV file: xf-arad6-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3627 0.09585 0.09126 -0.0201 1.0000 0.0664
-6.500 -0.3623 0.09362 0.08908 -0.0197 1.0000 0.0680
-6.250 -0.3608 0.09135 0.08686 -0.0201 1.0000 0.0699
-6.000 -0.3562 0.08912 0.08466 -0.0221 1.0000 0.0723
-5.750 -0.3276 0.08823 0.08368 -0.0379 1.0000 0.0748
-5.500 -0.3239 0.08358 0.07910 -0.0365 1.0000 0.0755
-5.250 -0.3253 0.07994 0.07553 -0.0314 1.0000 0.0767
-5.000 -0.3203 0.07715 0.07278 -0.0291 1.0000 0.0790
-4.750 -0.3070 0.07444 0.07007 -0.0306 1.0000 0.0834
-4.500 -0.2625 0.07059 0.06604 -0.0446 1.0000 0.0897
-4.250 -0.2597 0.06743 0.06295 -0.0410 1.0000 0.0915
-4.000 -0.2453 0.06470 0.06021 -0.0412 1.0000 0.0950
-3.750 -0.1929 0.06096 0.05620 -0.0540 1.0000 0.1040
-3.500 -0.1845 0.05792 0.05324 -0.0519 1.0000 0.1062
-3.250 -0.1630 0.05538 0.05067 -0.0534 1.0000 0.1117
-3.000 -0.1233 0.05198 0.04707 -0.0602 1.0000 0.1202
-2.750 -0.0998 0.04966 0.04470 -0.0615 1.0000 0.1270
-2.500 -0.0646 0.04679 0.04167 -0.0661 1.0000 0.1368
-2.250 -0.0328 0.04453 0.03929 -0.0693 1.0000 0.1511
-2.000 -0.0010 0.04239 0.03702 -0.0722 1.0000 0.1657
-1.750 0.0916 0.03367 0.02684 -0.0854 1.0000 0.0902
-1.500 0.1305 0.03093 0.02372 -0.0882 1.0000 0.0829
-1.250 0.1795 0.02850 0.02063 -0.0924 0.9983 0.0848
-1.000 0.2294 0.02673 0.01833 -0.0966 0.9957 0.0927
-0.750 0.2750 0.02592 0.01731 -0.1002 0.9917 0.1125
-0.500 0.3198 0.02549 0.01667 -0.1038 0.9868 0.1468
-0.250 0.3663 0.02502 0.01626 -0.1078 0.9832 0.1807
0.000 0.4056 0.02462 0.01589 -0.1105 0.9761 0.2121
0.250 0.4518 0.02424 0.01564 -0.1144 0.9718 0.2581
0.500 0.4904 0.02392 0.01551 -0.1169 0.9646 0.3202
0.750 0.5284 0.02228 0.01529 -0.1188 0.9592 1.0000
1.000 0.5651 0.02258 0.01531 -0.1208 0.9499 1.0000
1.250 0.6099 0.02275 0.01532 -0.1243 0.9432 1.0000
1.500 0.6438 0.02295 0.01544 -0.1257 0.9321 1.0000
1.750 0.6883 0.02264 0.01507 -0.1285 0.9191 1.0000
2.000 0.7407 0.02169 0.01407 -0.1319 0.9041 1.0000
2.250 0.7885 0.02087 0.01327 -0.1346 0.8913 1.0000
2.500 0.8309 0.02028 0.01270 -0.1365 0.8812 1.0000
2.750 0.8727 0.01958 0.01204 -0.1380 0.8715 1.0000
3.000 0.9059 0.01912 0.01165 -0.1380 0.8581 1.0000
3.250 0.9386 0.01860 0.01120 -0.1377 0.8441 1.0000
3.500 0.9709 0.01802 0.01068 -0.1371 0.8289 1.0000
3.750 0.9997 0.01757 0.01030 -0.1359 0.8106 1.0000
4.000 1.0272 0.01716 0.00999 -0.1345 0.7890 1.0000
4.250 1.0543 0.01679 0.00966 -0.1329 0.7639 1.0000
4.500 1.0802 0.01650 0.00939 -0.1312 0.7328 1.0000
4.750 1.1049 0.01634 0.00923 -0.1292 0.6924 1.0000
5.000 1.1275 0.01637 0.00912 -0.1269 0.6362 1.0000
5.250 1.1463 0.01680 0.00915 -0.1239 0.5463 1.0000
5.500 1.1593 0.01802 0.00959 -0.1205 0.4282 1.0000
5.750 1.1736 0.01951 0.01043 -0.1180 0.3530 1.0000
6.000 1.1913 0.02083 0.01141 -0.1162 0.3100 1.0000
6.250 1.2109 0.02207 0.01241 -0.1148 0.2797 1.0000
6.500 1.2317 0.02326 0.01345 -0.1136 0.2549 1.0000
6.750 1.2530 0.02448 0.01451 -0.1126 0.2341 1.0000
7.000 1.2746 0.02565 0.01565 -0.1115 0.2147 1.0000
7.250 1.2963 0.02683 0.01687 -0.1105 0.1972 1.0000
7.500 1.3177 0.02803 0.01807 -0.1095 0.1810 1.0000
7.750 1.3390 0.02929 0.01936 -0.1084 0.1663 1.0000
8.000 1.3603 0.03063 0.02076 -0.1074 0.1529 1.0000
8.250 1.3809 0.03199 0.02223 -0.1063 0.1405 1.0000
8.500 1.4031 0.03362 0.02389 -0.1054 0.1301 1.0000
8.750 1.4248 0.03521 0.02542 -0.1046 0.1200 1.0000
9.000 1.4419 0.03662 0.02722 -0.1027 0.1107 1.0000
9.250 1.4621 0.03871 0.02946 -0.1015 0.1029 1.0000
9.500 1.4797 0.04016 0.03097 -0.1001 0.0946 1.0000
9.750 1.4927 0.04229 0.03353 -0.0978 0.0870 1.0000
10.000 1.5063 0.04402 0.03526 -0.0960 0.0791 1.0000
10.250 1.5139 0.04533 0.03688 -0.0930 0.0717 1.0000
10.500 1.5212 0.04791 0.03971 -0.0904 0.0653 1.0000
10.750 1.5272 0.04967 0.04166 -0.0874 0.0594 1.0000
11.000 1.5305 0.05345 0.04570 -0.0845 0.0554 1.0000
11.250 1.5229 0.05655 0.04934 -0.0799 0.0525 1.0000
11.500 1.5199 0.05873 0.05171 -0.0762 0.0493 1.0000
11.750 1.5232 0.06175 0.05469 -0.0742 0.0463 1.0000
12.000 1.5050 0.06569 0.05899 -0.0694 0.0456 1.0000
12.250 1.4841 0.06941 0.06310 -0.0651 0.0453 1.0000
12.500 1.4621 0.07368 0.06772 -0.0619 0.0451 1.0000
12.750 1.4388 0.07846 0.07282 -0.0597 0.0450 1.0000
13.000 1.4144 0.08380 0.07844 -0.0586 0.0450 1.0000
13.250 1.3895 0.08970 0.08460 -0.0587 0.0452 1.0000
13.500 1.3643 0.09626 0.09135 -0.0601 0.0454 1.0000
13.750 1.3392 0.10348 0.09876 -0.0627 0.0456 1.0000
14.000 1.3154 0.11135 0.10678 -0.0662 0.0459 1.0000
14.250 1.2177 0.14179 0.13768 -0.0890 0.0574 1.0000
14.500 1.1640 0.17119 0.16688 -0.1068 0.0691 1.0000
14.750 1.1621 0.17820 0.17388 -0.1096 0.0688 1.0000
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Polar data table (+)
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