E591 (e591-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 50,000 Max Cl/Cd: 10.01 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e591-il-50000.txt Download as CSV file: xf-e591-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E591
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2845 0.13271 0.12742 -0.0098 1.0000 0.2123
-7.000 -0.3051 0.13332 0.12814 -0.0086 1.0000 0.2172
-6.750 -0.3423 0.13584 0.13080 -0.0074 1.0000 0.2190
-6.500 -0.3241 0.13065 0.12565 -0.0059 1.0000 0.2221
-6.250 -0.3066 0.12763 0.12265 -0.0063 0.9971 0.2296
-6.000 -0.3249 0.12919 0.12428 -0.0117 0.9864 0.2373
-5.750 -0.2663 0.12157 0.11660 -0.0156 0.9771 0.2475
-5.500 -0.2903 0.12307 0.11818 -0.0181 0.9658 0.2560
-5.250 -0.2424 0.11645 0.11152 -0.0214 0.9563 0.2643
-5.000 -0.2541 0.11639 0.11151 -0.0224 0.9450 0.2741
-4.750 -0.2424 0.11315 0.10830 -0.0250 0.9356 0.2793
-4.500 -0.2208 0.10980 0.10494 -0.0259 0.9248 0.2872
-4.250 -0.2525 0.11115 0.10640 -0.0299 0.9123 0.2964
-4.000 -0.2143 0.10542 0.10064 -0.0291 0.9042 0.3013
-3.750 -0.2055 0.10323 0.09846 -0.0295 0.8935 0.3087
-3.500 -0.2145 0.10179 0.09707 -0.0329 0.8826 0.3184
-3.250 -0.1252 0.06923 0.06353 -0.0956 0.8795 0.1461
-3.000 0.0056 0.05529 0.04805 -0.1277 0.8736 0.1425
-2.750 0.0569 0.05232 0.04427 -0.1351 0.8628 0.1509
-2.500 0.1236 0.05016 0.04170 -0.1423 0.8548 0.1677
-2.250 0.1446 0.04985 0.04146 -0.1423 0.8424 0.1804
-2.000 0.1917 0.04912 0.04077 -0.1456 0.8333 0.2108
-1.750 0.2237 0.04905 0.04079 -0.1468 0.8220 0.2582
-1.500 0.2480 0.04995 0.04214 -0.1455 0.8114 0.3273
-1.250 0.2736 0.05099 0.04337 -0.1437 0.8012 0.4020
-1.000 0.2839 0.05224 0.04472 -0.1407 0.7902 0.4435
-0.750 0.3096 0.05280 0.04535 -0.1384 0.7810 0.4878
-0.500 0.3148 0.05393 0.04653 -0.1353 0.7700 0.5123
-0.250 0.3490 0.05405 0.04656 -0.1350 0.7615 0.5510
0.000 0.3565 0.05519 0.04769 -0.1331 0.7503 0.5716
0.250 0.3948 0.05510 0.04747 -0.1338 0.7420 0.6028
0.500 0.4008 0.05645 0.04881 -0.1323 0.7311 0.6192
0.750 0.4440 0.05635 0.04854 -0.1343 0.7227 0.6489
1.000 0.4497 0.05796 0.05012 -0.1331 0.7119 0.6657
1.250 0.4843 0.05801 0.05007 -0.1336 0.7037 0.6916
1.500 0.4909 0.05972 0.05176 -0.1326 0.6936 0.7100
1.750 0.5187 0.06010 0.05208 -0.1325 0.6851 0.7371
2.000 0.5305 0.06161 0.05357 -0.1319 0.6761 0.7615
2.250 0.5441 0.06264 0.05461 -0.1308 0.6672 0.7885
2.500 0.5691 0.06278 0.05475 -0.1297 0.6599 0.8291
2.750 0.5571 0.06528 0.05736 -0.1274 0.6508 0.8575
3.000 0.6000 0.06434 0.05642 -0.1287 0.6433 1.0000
3.250 0.6011 0.06854 0.06055 -0.1318 0.6328 1.0000
3.500 0.6869 0.06864 0.06017 -0.1404 0.6236 1.0000
3.750 0.6633 0.07363 0.06518 -0.1399 0.6147 1.0000
4.000 0.7073 0.07467 0.06595 -0.1426 0.6061 1.0000
4.250 0.7066 0.07838 0.06960 -0.1428 0.5989 1.0000
4.500 0.7085 0.08181 0.07298 -0.1431 0.5920 1.0000
4.750 0.7605 0.08203 0.07296 -0.1446 0.5833 1.0000
5.000 0.7350 0.08747 0.07847 -0.1442 0.5790 1.0000
5.250 0.7323 0.09145 0.08244 -0.1445 0.5751 1.0000
5.500 0.7862 0.09147 0.08226 -0.1454 0.5641 1.0000
5.750 0.7708 0.09661 0.08745 -0.1456 0.5625 1.0000
6.000 0.7688 0.10106 0.09190 -0.1463 0.5625 1.0000
6.250 0.7748 0.10526 0.09611 -0.1474 0.5635 1.0000
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Polar data table (+)
Polar graphs
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