ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 500,000 Max Cl/Cd: 105.58 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad6-il-500000-n5.txt Download as CSV file: xf-arad6-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3526 0.10949 0.10713 -0.0289 1.0000 0.0120
-9.000 -0.3530 0.10691 0.10457 -0.0286 1.0000 0.0120
-8.750 -0.3560 0.10460 0.10230 -0.0276 1.0000 0.0120
-8.500 -0.3473 0.10097 0.09868 -0.0301 0.9982 0.0120
-8.250 -0.3350 0.09696 0.09467 -0.0338 0.9957 0.0120
-7.250 -0.2742 0.08020 0.07791 -0.0514 0.9832 0.0125
-7.000 -0.2558 0.07814 0.07585 -0.0535 0.9797 0.0132
-6.750 -0.2332 0.07485 0.07255 -0.0586 0.9762 0.0147
-6.250 -0.1784 0.06213 0.05973 -0.0771 0.9663 0.0118
-6.000 -0.1486 0.05715 0.05469 -0.0845 0.9621 0.0117
-5.750 -0.1131 0.05131 0.04877 -0.0935 0.9587 0.0117
-5.500 -0.0770 0.04512 0.04246 -0.1020 0.9530 0.0119
-5.000 0.0389 0.01667 0.01206 -0.1323 0.9483 0.0122
-4.750 0.0715 0.01450 0.00943 -0.1340 0.9451 0.0124
-4.500 0.1012 0.01325 0.00791 -0.1347 0.9397 0.0127
-4.250 0.1307 0.01246 0.00695 -0.1351 0.9346 0.0131
-4.000 0.1601 0.01185 0.00620 -0.1354 0.9303 0.0136
-3.750 0.1888 0.01133 0.00558 -0.1356 0.9242 0.0140
-3.500 0.2177 0.01087 0.00501 -0.1357 0.9187 0.0145
-3.250 0.2466 0.01047 0.00451 -0.1358 0.9130 0.0150
-3.000 0.2753 0.01013 0.00411 -0.1359 0.9066 0.0157
-2.750 0.3038 0.00989 0.00380 -0.1359 0.9006 0.0164
-2.500 0.3327 0.00954 0.00338 -0.1360 0.8935 0.0175
-2.250 0.3613 0.00930 0.00308 -0.1360 0.8869 0.0188
-2.000 0.3899 0.00910 0.00285 -0.1361 0.8791 0.0209
-1.750 0.4185 0.00891 0.00266 -0.1361 0.8718 0.0271
-1.500 0.4470 0.00875 0.00252 -0.1361 0.8633 0.0420
-1.250 0.4754 0.00865 0.00243 -0.1361 0.8551 0.0548
-1.000 0.5037 0.00855 0.00237 -0.1361 0.8463 0.0732
-0.750 0.5321 0.00848 0.00232 -0.1362 0.8369 0.0897
-0.500 0.5601 0.00842 0.00228 -0.1361 0.8242 0.1098
-0.250 0.5873 0.00843 0.00222 -0.1357 0.8023 0.1261
0.000 0.6145 0.00846 0.00217 -0.1354 0.7771 0.1398
0.250 0.6420 0.00851 0.00215 -0.1352 0.7563 0.1544
0.500 0.6694 0.00857 0.00216 -0.1350 0.7323 0.1732
0.750 0.6967 0.00863 0.00219 -0.1349 0.7082 0.1996
1.000 0.7242 0.00869 0.00223 -0.1348 0.6867 0.2346
1.250 0.7519 0.00869 0.00231 -0.1348 0.6651 0.2956
1.750 0.7992 0.00757 0.00244 -0.1331 0.6168 1.0000
2.000 0.8259 0.00783 0.00253 -0.1328 0.5860 1.0000
2.250 0.8523 0.00813 0.00264 -0.1325 0.5512 1.0000
2.500 0.8782 0.00849 0.00279 -0.1321 0.5090 1.0000
2.750 0.9034 0.00896 0.00300 -0.1317 0.4550 1.0000
3.000 0.9279 0.00953 0.00325 -0.1312 0.3919 1.0000
3.250 0.9522 0.01015 0.00354 -0.1307 0.3271 1.0000
3.500 0.9772 0.01066 0.00382 -0.1303 0.2830 1.0000
3.750 1.0025 0.01111 0.00410 -0.1300 0.2495 1.0000
4.000 1.0282 0.01148 0.00436 -0.1297 0.2249 1.0000
4.250 1.0539 0.01184 0.00461 -0.1294 0.2052 1.0000
4.500 1.0798 0.01217 0.00487 -0.1291 0.1887 1.0000
4.750 1.1055 0.01249 0.00514 -0.1288 0.1746 1.0000
5.000 1.1311 0.01282 0.00542 -0.1285 0.1616 1.0000
5.250 1.1567 0.01314 0.00570 -0.1281 0.1513 1.0000
5.500 1.1822 0.01344 0.00598 -0.1278 0.1412 1.0000
5.750 1.2073 0.01380 0.00631 -0.1274 0.1289 1.0000
6.000 1.2321 0.01416 0.00664 -0.1269 0.1177 1.0000
6.250 1.2567 0.01454 0.00698 -0.1264 0.1081 1.0000
6.500 1.2814 0.01489 0.00733 -0.1259 0.0996 1.0000
6.750 1.3056 0.01529 0.00773 -0.1254 0.0909 1.0000
7.000 1.3292 0.01573 0.00814 -0.1248 0.0820 1.0000
7.250 1.3530 0.01614 0.00856 -0.1241 0.0747 1.0000
7.500 1.3761 0.01660 0.00901 -0.1234 0.0672 1.0000
7.750 1.3985 0.01713 0.00952 -0.1226 0.0585 1.0000
8.000 1.4209 0.01762 0.01001 -0.1218 0.0516 1.0000
8.250 1.4428 0.01815 0.01055 -0.1209 0.0454 1.0000
8.500 1.4641 0.01872 0.01111 -0.1199 0.0396 1.0000
8.750 1.4856 0.01925 0.01168 -0.1189 0.0356 1.0000
9.000 1.5061 0.01984 0.01230 -0.1178 0.0311 1.0000
9.250 1.5261 0.02044 0.01294 -0.1166 0.0273 1.0000
9.500 1.5454 0.02108 0.01360 -0.1153 0.0233 1.0000
9.750 1.5638 0.02177 0.01432 -0.1138 0.0195 1.0000
10.000 1.5807 0.02256 0.01512 -0.1122 0.0153 1.0000
10.500 1.6110 0.02432 0.01697 -0.1082 0.0088 1.0000
10.750 1.6246 0.02525 0.01797 -0.1060 0.0075 1.0000
11.000 1.6372 0.02618 0.01900 -0.1036 0.0067 1.0000
11.250 1.6463 0.02719 0.02011 -0.1007 0.0062 1.0000
11.500 1.6542 0.02836 0.02138 -0.0976 0.0057 1.0000
11.750 1.6620 0.02956 0.02271 -0.0947 0.0054 1.0000
12.000 1.6705 0.03074 0.02402 -0.0921 0.0051 1.0000
12.250 1.6779 0.03203 0.02544 -0.0895 0.0049 1.0000
12.500 1.6844 0.03343 0.02698 -0.0869 0.0046 1.0000
12.750 1.6896 0.03496 0.02865 -0.0843 0.0044 1.0000
13.000 1.6934 0.03668 0.03051 -0.0818 0.0043 1.0000
13.250 1.6958 0.03858 0.03255 -0.0793 0.0041 1.0000
13.500 1.6962 0.04071 0.03483 -0.0769 0.0040 1.0000
13.750 1.6947 0.04314 0.03740 -0.0747 0.0039 1.0000
14.000 1.6910 0.04590 0.04032 -0.0726 0.0038 1.0000
14.250 1.6846 0.04906 0.04365 -0.0708 0.0037 1.0000
14.500 1.6752 0.05278 0.04754 -0.0694 0.0036 1.0000
14.750 1.6642 0.05693 0.05187 -0.0684 0.0036 1.0000
15.000 1.6544 0.06114 0.05625 -0.0680 0.0035 1.0000
15.250 1.6446 0.06563 0.06091 -0.0681 0.0035 1.0000
15.500 1.6329 0.07073 0.06618 -0.0688 0.0035 1.0000
15.750 1.6190 0.07649 0.07212 -0.0701 0.0035 1.0000
16.000 1.6027 0.08302 0.07883 -0.0722 0.0035 1.0000
16.250 1.5843 0.09035 0.08634 -0.0751 0.0034 1.0000
16.500 1.5631 0.09864 0.09482 -0.0787 0.0034 1.0000
16.750 1.5392 0.10790 0.10427 -0.0832 0.0035 1.0000
17.000 1.5131 0.11806 0.11461 -0.0884 0.0035 1.0000
17.250 1.4867 0.12859 0.12531 -0.0938 0.0035 1.0000
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Polar data table (+)
Polar graphs
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