ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 200,000 Max Cl/Cd: 85.99 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad6-il-200000-n5.txt Download as CSV file: xf-arad6-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2751 0.10181 0.09850 -0.0275 1.0000 0.0237
-8.750 -0.2763 0.09966 0.09638 -0.0262 1.0000 0.0246
-8.500 -0.3511 0.10542 0.10184 -0.0283 1.0000 0.0227
-8.250 -0.3473 0.10301 0.09946 -0.0266 1.0000 0.0235
-8.000 -0.3491 0.10120 0.09770 -0.0249 1.0000 0.0242
-7.750 -0.3546 0.09964 0.09619 -0.0228 1.0000 0.0250
-7.500 -0.3637 0.09829 0.09490 -0.0201 1.0000 0.0256
-7.250 -0.3589 0.09553 0.09217 -0.0216 0.9978 0.0266
-7.000 -0.3371 0.09122 0.08784 -0.0284 0.9939 0.0279
-6.750 -0.3062 0.08667 0.08326 -0.0414 0.9882 0.0292
-6.500 -0.2745 0.08174 0.07829 -0.0510 0.9851 0.0294
-6.250 -0.2482 0.07719 0.07371 -0.0576 0.9804 0.0295
-6.000 -0.2183 0.07235 0.06881 -0.0645 0.9769 0.0295
-5.750 -0.1855 0.06730 0.06369 -0.0718 0.9744 0.0295
-5.250 -0.1465 0.05935 0.05571 -0.0758 0.9671 0.0264
-4.750 -0.0455 0.04437 0.04030 -0.0997 0.9624 0.0217
-4.500 -0.0005 0.03908 0.03480 -0.1076 0.9610 0.0211
-4.250 0.0506 0.03233 0.02768 -0.1165 0.9600 0.0206
-4.000 0.1082 0.02197 0.01615 -0.1263 0.9596 0.0204
-3.750 0.1444 0.01898 0.01247 -0.1287 0.9559 0.0209
-3.500 0.1784 0.01758 0.01064 -0.1301 0.9521 0.0223
-3.250 0.2130 0.01641 0.00928 -0.1318 0.9491 0.0238
-3.000 0.2482 0.01546 0.00815 -0.1334 0.9466 0.0248
-2.750 0.2813 0.01471 0.00727 -0.1344 0.9429 0.0261
-2.500 0.3120 0.01412 0.00657 -0.1349 0.9373 0.0279
-2.250 0.3454 0.01353 0.00589 -0.1360 0.9335 0.0310
-2.000 0.3780 0.01314 0.00546 -0.1368 0.9294 0.0388
-1.750 0.4072 0.01278 0.00516 -0.1371 0.9226 0.0546
-1.500 0.4391 0.01251 0.00491 -0.1378 0.9179 0.0731
-1.250 0.4677 0.01238 0.00485 -0.1379 0.9108 0.0960
-1.000 0.4979 0.01220 0.00469 -0.1382 0.9047 0.1141
-0.750 0.5269 0.01205 0.00455 -0.1383 0.8974 0.1307
-0.500 0.5562 0.01190 0.00442 -0.1385 0.8904 0.1486
-0.250 0.5848 0.01177 0.00435 -0.1385 0.8824 0.1697
0.000 0.6139 0.01163 0.00426 -0.1386 0.8750 0.1945
0.250 0.6419 0.01151 0.00424 -0.1385 0.8658 0.2259
0.500 0.6699 0.01130 0.00416 -0.1383 0.8540 0.2768
0.750 0.6920 0.01004 0.00414 -0.1368 0.8375 0.7778
1.250 0.7426 0.00973 0.00371 -0.1345 0.7966 1.0000
1.500 0.7697 0.00980 0.00365 -0.1340 0.7759 1.0000
1.750 0.7969 0.00990 0.00365 -0.1335 0.7567 1.0000
2.000 0.8240 0.01003 0.00368 -0.1332 0.7377 1.0000
2.250 0.8509 0.01018 0.00372 -0.1327 0.7166 1.0000
2.500 0.8775 0.01035 0.00379 -0.1322 0.6933 1.0000
2.750 0.9038 0.01056 0.00389 -0.1317 0.6667 1.0000
3.000 0.9296 0.01081 0.00401 -0.1311 0.6362 1.0000
3.250 0.9547 0.01113 0.00415 -0.1304 0.6004 1.0000
3.500 0.9791 0.01151 0.00433 -0.1295 0.5574 1.0000
3.750 1.0022 0.01201 0.00459 -0.1285 0.5027 1.0000
4.000 1.0238 0.01268 0.00491 -0.1274 0.4359 1.0000
4.250 1.0446 0.01349 0.00533 -0.1262 0.3638 1.0000
4.500 1.0659 0.01427 0.00580 -0.1252 0.3061 1.0000
4.750 1.0883 0.01495 0.00629 -0.1243 0.2669 1.0000
5.000 1.1113 0.01554 0.00675 -0.1236 0.2390 1.0000
5.250 1.1347 0.01609 0.00721 -0.1229 0.2177 1.0000
5.500 1.1581 0.01661 0.00767 -0.1223 0.1995 1.0000
5.750 1.1815 0.01712 0.00817 -0.1216 0.1840 1.0000
6.000 1.2047 0.01763 0.00866 -0.1208 0.1699 1.0000
6.250 1.2278 0.01814 0.00916 -0.1201 0.1578 1.0000
6.500 1.2505 0.01867 0.00969 -0.1193 0.1462 1.0000
6.750 1.2729 0.01922 0.01023 -0.1184 0.1344 1.0000
7.000 1.2950 0.01978 0.01082 -0.1176 0.1229 1.0000
7.250 1.3171 0.02032 0.01140 -0.1167 0.1122 1.0000
7.500 1.3386 0.02091 0.01202 -0.1157 0.1027 1.0000
7.750 1.3592 0.02158 0.01270 -0.1146 0.0944 1.0000
8.000 1.3799 0.02221 0.01342 -0.1134 0.0861 1.0000
8.250 1.3996 0.02291 0.01417 -0.1122 0.0787 1.0000
8.500 1.4184 0.02369 0.01497 -0.1108 0.0717 1.0000
8.750 1.4371 0.02444 0.01583 -0.1094 0.0663 1.0000
9.000 1.4545 0.02526 0.01670 -0.1078 0.0603 1.0000
9.250 1.4719 0.02605 0.01761 -0.1062 0.0544 1.0000
9.500 1.4873 0.02696 0.01852 -0.1044 0.0481 1.0000
9.750 1.5043 0.02771 0.01939 -0.1028 0.0426 1.0000
10.000 1.5176 0.02873 0.02041 -0.1008 0.0376 1.0000
10.250 1.5324 0.02957 0.02142 -0.0988 0.0335 1.0000
10.500 1.5427 0.03063 0.02254 -0.0962 0.0296 1.0000
10.750 1.5527 0.03176 0.02381 -0.0936 0.0264 1.0000
11.000 1.5621 0.03298 0.02518 -0.0911 0.0228 1.0000
11.250 1.5685 0.03450 0.02679 -0.0883 0.0198 1.0000
11.500 1.5754 0.03600 0.02844 -0.0857 0.0170 1.0000
11.750 1.5789 0.03783 0.03036 -0.0830 0.0149 1.0000
12.000 1.5832 0.03960 0.03232 -0.0804 0.0133 1.0000
12.250 1.5862 0.04154 0.03440 -0.0780 0.0121 1.0000
12.500 1.5853 0.04389 0.03689 -0.0755 0.0114 1.0000
12.750 1.5833 0.04643 0.03961 -0.0731 0.0108 1.0000
13.000 1.5808 0.04912 0.04252 -0.0711 0.0104 1.0000
13.250 1.5768 0.05209 0.04569 -0.0693 0.0100 1.0000
13.500 1.5713 0.05536 0.04917 -0.0679 0.0097 1.0000
13.750 1.5644 0.05897 0.05301 -0.0668 0.0094 1.0000
14.000 1.5560 0.06295 0.05719 -0.0662 0.0092 1.0000
14.250 1.5460 0.06738 0.06181 -0.0661 0.0090 1.0000
14.500 1.5344 0.07228 0.06692 -0.0665 0.0088 1.0000
14.750 1.5210 0.07776 0.07260 -0.0676 0.0087 1.0000
15.000 1.5065 0.08382 0.07886 -0.0694 0.0086 1.0000
15.250 1.4905 0.09056 0.08580 -0.0719 0.0086 1.0000
15.500 1.4729 0.09798 0.09342 -0.0751 0.0086 1.0000
15.750 1.4544 0.10606 0.10170 -0.0791 0.0086 1.0000
16.000 1.4351 0.11473 0.11056 -0.0836 0.0086 1.0000
16.250 1.4153 0.12389 0.11992 -0.0886 0.0086 1.0000
16.500 1.3955 0.13335 0.12955 -0.0939 0.0087 1.0000
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