ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.97 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad6-il-1000000-n5.txt Download as CSV file: xf-arad6-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3660 0.11505 0.11332 -0.0267 1.0000 0.0053
-9.750 -0.3638 0.11136 0.10965 -0.0275 1.0000 0.0056
-9.500 -0.3656 0.10727 0.10557 -0.0282 1.0000 0.0061
-9.250 -0.3603 0.10417 0.10249 -0.0294 0.9993 0.0061
-9.000 -0.3480 0.10107 0.09939 -0.0320 0.9975 0.0062
-8.750 -0.3352 0.09784 0.09616 -0.0349 0.9957 0.0063
-8.500 -0.3224 0.09454 0.09286 -0.0380 0.9936 0.0064
-8.250 -0.3107 0.09119 0.08952 -0.0409 0.9896 0.0066
-8.000 -0.2979 0.08766 0.08599 -0.0443 0.9857 0.0068
-7.750 -0.2875 0.08427 0.08260 -0.0472 0.9791 0.0070
-7.500 -0.2717 0.08034 0.07867 -0.0519 0.9740 0.0072
-7.250 -0.2567 0.07643 0.07474 -0.0564 0.9670 0.0073
-7.000 -0.2392 0.07225 0.07054 -0.0616 0.9606 0.0074
-6.750 -0.2203 0.06785 0.06611 -0.0672 0.9535 0.0077
-6.500 -0.1979 0.06268 0.06089 -0.0741 0.9466 0.0080
-6.000 -0.0776 0.01519 0.01145 -0.1298 0.9358 0.0088
-5.750 -0.0476 0.01349 0.00942 -0.1310 0.9314 0.0091
-5.500 -0.0183 0.01264 0.00841 -0.1316 0.9264 0.0093
-5.250 0.0109 0.01188 0.00747 -0.1321 0.9210 0.0095
-5.000 0.0399 0.01122 0.00666 -0.1324 0.9161 0.0097
-4.750 0.0692 0.01064 0.00595 -0.1328 0.9105 0.0098
-4.500 0.0982 0.01017 0.00536 -0.1330 0.9046 0.0101
-4.250 0.1272 0.00975 0.00483 -0.1333 0.8989 0.0105
-4.000 0.1563 0.00938 0.00437 -0.1335 0.8923 0.0108
-3.750 0.1852 0.00907 0.00397 -0.1336 0.8861 0.0112
-3.500 0.2142 0.00879 0.00362 -0.1338 0.8789 0.0115
-3.250 0.2429 0.00856 0.00331 -0.1339 0.8719 0.0117
-3.000 0.2718 0.00836 0.00306 -0.1341 0.8640 0.0120
-2.750 0.3006 0.00818 0.00281 -0.1342 0.8562 0.0121
-2.500 0.3296 0.00794 0.00250 -0.1343 0.8476 0.0127
-2.250 0.3585 0.00777 0.00228 -0.1345 0.8392 0.0137
-2.000 0.3872 0.00766 0.00212 -0.1345 0.8301 0.0148
-1.750 0.4160 0.00756 0.00198 -0.1346 0.8204 0.0159
-1.500 0.4448 0.00747 0.00186 -0.1347 0.8109 0.0196
-1.250 0.4734 0.00736 0.00177 -0.1348 0.7993 0.0351
-1.000 0.5012 0.00737 0.00171 -0.1347 0.7747 0.0459
-0.750 0.5287 0.00744 0.00167 -0.1346 0.7440 0.0574
-0.500 0.5567 0.00747 0.00166 -0.1346 0.7196 0.0724
-0.250 0.5845 0.00753 0.00166 -0.1345 0.6944 0.0902
0.000 0.6123 0.00761 0.00169 -0.1345 0.6675 0.1105
0.250 0.6400 0.00772 0.00172 -0.1345 0.6407 0.1260
0.500 0.6680 0.00781 0.00175 -0.1345 0.6189 0.1378
0.750 0.6957 0.00793 0.00180 -0.1345 0.5937 0.1505
1.000 0.7234 0.00807 0.00186 -0.1345 0.5668 0.1660
1.250 0.7509 0.00821 0.00195 -0.1345 0.5358 0.1938
1.500 0.7780 0.00843 0.00207 -0.1344 0.4970 0.2239
1.750 0.8050 0.00864 0.00221 -0.1344 0.4561 0.2669
2.000 0.8317 0.00887 0.00241 -0.1344 0.4030 0.3686
2.250 0.8520 0.00804 0.00264 -0.1332 0.3478 1.0000
2.500 0.8778 0.00853 0.00285 -0.1330 0.2933 1.0000
2.750 0.9045 0.00886 0.00303 -0.1328 0.2620 1.0000
3.000 0.9313 0.00916 0.00320 -0.1327 0.2366 1.0000
3.250 0.9580 0.00944 0.00336 -0.1326 0.2141 1.0000
3.500 0.9849 0.00969 0.00353 -0.1325 0.1972 1.0000
3.750 1.0116 0.00996 0.00371 -0.1323 0.1808 1.0000
4.000 1.0385 0.01019 0.00388 -0.1322 0.1686 1.0000
4.250 1.0652 0.01043 0.00407 -0.1320 0.1562 1.0000
4.500 1.0918 0.01067 0.00426 -0.1319 0.1470 1.0000
4.750 1.1184 0.01090 0.00446 -0.1317 0.1383 1.0000
5.000 1.1449 0.01114 0.00466 -0.1315 0.1286 1.0000
5.250 1.1708 0.01144 0.00489 -0.1312 0.1157 1.0000
5.500 1.1968 0.01172 0.00514 -0.1310 0.1066 1.0000
5.750 1.2226 0.01201 0.00539 -0.1307 0.0982 1.0000
6.000 1.2483 0.01229 0.00565 -0.1304 0.0899 1.0000
6.250 1.2736 0.01262 0.00593 -0.1300 0.0811 1.0000
6.500 1.2989 0.01293 0.00624 -0.1297 0.0743 1.0000
6.750 1.3237 0.01329 0.00655 -0.1292 0.0656 1.0000
7.000 1.3480 0.01370 0.00691 -0.1287 0.0562 1.0000
7.250 1.3721 0.01411 0.00729 -0.1282 0.0489 1.0000
7.500 1.3965 0.01447 0.00764 -0.1276 0.0439 1.0000
7.750 1.4200 0.01491 0.00806 -0.1270 0.0377 1.0000
8.000 1.4437 0.01530 0.00845 -0.1264 0.0335 1.0000
8.250 1.4665 0.01579 0.00891 -0.1256 0.0279 1.0000
8.500 1.4895 0.01623 0.00936 -0.1249 0.0244 1.0000
8.750 1.5117 0.01673 0.00986 -0.1241 0.0207 1.0000
9.000 1.5340 0.01720 0.01035 -0.1232 0.0178 1.0000
9.250 1.5550 0.01778 0.01092 -0.1222 0.0136 1.0000
9.500 1.5742 0.01854 0.01165 -0.1208 0.0083 1.0000
9.750 1.5937 0.01921 0.01234 -0.1195 0.0062 1.0000
10.000 1.6132 0.01984 0.01302 -0.1182 0.0052 1.0000
10.250 1.6324 0.02046 0.01370 -0.1169 0.0047 1.0000
10.500 1.6504 0.02114 0.01444 -0.1153 0.0042 1.0000
10.750 1.6673 0.02188 0.01525 -0.1136 0.0038 1.0000
11.000 1.6832 0.02265 0.01609 -0.1117 0.0035 1.0000
11.250 1.6993 0.02333 0.01685 -0.1099 0.0034 1.0000
11.500 1.7141 0.02407 0.01767 -0.1078 0.0033 1.0000
11.750 1.7273 0.02487 0.01855 -0.1056 0.0032 1.0000
12.000 1.7370 0.02572 0.01950 -0.1026 0.0031 1.0000
12.250 1.7460 0.02665 0.02053 -0.0997 0.0029 1.0000
12.500 1.7548 0.02766 0.02163 -0.0969 0.0028 1.0000
12.750 1.7631 0.02875 0.02282 -0.0942 0.0027 1.0000
13.000 1.7705 0.02995 0.02411 -0.0915 0.0027 1.0000
13.250 1.7770 0.03126 0.02552 -0.0888 0.0026 1.0000
13.500 1.7823 0.03270 0.02707 -0.0862 0.0025 1.0000
13.750 1.7862 0.03430 0.02878 -0.0836 0.0024 1.0000
14.000 1.7887 0.03610 0.03070 -0.0810 0.0023 1.0000
14.250 1.7891 0.03813 0.03286 -0.0785 0.0023 1.0000
14.500 1.7868 0.04052 0.03538 -0.0760 0.0022 1.0000
14.750 1.7824 0.04323 0.03826 -0.0737 0.0021 1.0000
15.000 1.7751 0.04638 0.04157 -0.0716 0.0021 1.0000
15.250 1.7710 0.04934 0.04466 -0.0701 0.0021 1.0000
15.500 1.7667 0.05247 0.04793 -0.0690 0.0021 1.0000
15.750 1.7604 0.05600 0.05160 -0.0682 0.0020 1.0000
16.000 1.7518 0.06002 0.05576 -0.0678 0.0020 1.0000
16.250 1.7422 0.06445 0.06033 -0.0679 0.0020 1.0000
16.500 1.7304 0.06950 0.06553 -0.0685 0.0020 1.0000
16.750 1.7159 0.07522 0.07142 -0.0697 0.0020 1.0000
17.000 1.6973 0.08200 0.07836 -0.0718 0.0020 1.0000
17.250 1.6761 0.08966 0.08620 -0.0747 0.0020 1.0000
17.500 1.6509 0.09853 0.09524 -0.0785 0.0020 1.0000
17.750 1.6189 0.10920 0.10610 -0.0836 0.0020 1.0000
18.000 1.5827 0.12141 0.11850 -0.0898 0.0020 1.0000
18.250 1.5405 0.13526 0.13256 -0.0971 0.0020 1.0000
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