EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 50,000 Max Cl/Cd: 17.95 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea81006-il-50000.txt Download as CSV file: xf-ea81006-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 8(-1)-006 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5485 0.11191 0.10528 0.0175 1.0000 0.2852
-9.250 -0.5433 0.10781 0.10119 0.0178 1.0000 0.2994
-9.000 -0.6435 0.11012 0.10309 0.0241 1.0000 0.2988
-8.750 -0.6408 0.10655 0.09956 0.0242 1.0000 0.3131
-8.500 -0.6228 0.10159 0.09458 0.0257 1.0000 0.3325
-8.250 -0.6198 0.09848 0.09152 0.0265 1.0000 0.3538
-8.000 -0.6332 0.09656 0.08970 0.0266 1.0000 0.3708
-7.750 -0.6040 0.09100 0.08407 0.0282 1.0000 0.3920
-7.500 -0.6142 0.08881 0.08195 0.0293 1.0000 0.4141
-7.250 -0.5959 0.08465 0.07776 0.0309 1.0000 0.4396
-6.000 -0.6339 0.05029 0.04238 -0.0100 1.0000 0.1813
-5.750 -0.6180 0.04420 0.03540 -0.0109 1.0000 0.1591
-5.500 -0.5991 0.04052 0.03105 -0.0102 1.0000 0.1570
-5.250 -0.5781 0.03701 0.02711 -0.0093 1.0000 0.1563
-5.000 -0.5552 0.03376 0.02343 -0.0083 1.0000 0.1543
-4.750 -0.5320 0.03125 0.02034 -0.0073 1.0000 0.1585
-4.500 -0.5072 0.02899 0.01790 -0.0064 1.0000 0.1624
-4.250 -0.4806 0.02694 0.01551 -0.0056 1.0000 0.1642
-4.000 -0.4535 0.02526 0.01353 -0.0047 1.0000 0.1682
-3.750 -0.4272 0.02386 0.01208 -0.0040 1.0000 0.1779
-3.500 -0.3985 0.02261 0.01058 -0.0033 1.0000 0.1850
-3.250 -0.3696 0.02137 0.00939 -0.0028 1.0000 0.1933
-3.000 -0.3429 0.02029 0.00833 -0.0021 1.0000 0.2061
-2.750 -0.3200 0.01926 0.00739 -0.0008 1.0000 0.2281
-2.500 -0.1757 0.01602 0.00674 -0.0165 1.0000 1.0000
-2.250 -0.1571 0.01579 0.00626 -0.0151 1.0000 1.0000
-2.000 -0.1387 0.01558 0.00586 -0.0137 1.0000 1.0000
-1.750 -0.1205 0.01541 0.00549 -0.0123 1.0000 1.0000
-1.500 -0.1025 0.01526 0.00520 -0.0107 1.0000 1.0000
-1.250 -0.0848 0.01513 0.00497 -0.0091 1.0000 1.0000
-1.000 -0.0674 0.01503 0.00478 -0.0074 1.0000 1.0000
-0.750 -0.0503 0.01496 0.00464 -0.0056 1.0000 1.0000
-0.500 -0.0335 0.01490 0.00453 -0.0037 1.0000 1.0000
-0.250 -0.0167 0.01487 0.00447 -0.0019 1.0000 1.0000
0.000 0.0000 0.01486 0.00445 0.0000 1.0000 1.0000
0.250 0.0167 0.01487 0.00447 0.0019 1.0000 1.0000
0.500 0.0335 0.01490 0.00453 0.0037 1.0000 1.0000
0.750 0.0503 0.01495 0.00464 0.0056 1.0000 1.0000
1.000 0.0674 0.01503 0.00478 0.0074 1.0000 1.0000
1.250 0.0848 0.01513 0.00497 0.0091 1.0000 1.0000
1.500 0.1025 0.01526 0.00520 0.0107 1.0000 1.0000
1.750 0.1205 0.01540 0.00549 0.0123 1.0000 1.0000
2.000 0.1387 0.01558 0.00586 0.0137 1.0000 1.0000
2.250 0.1571 0.01578 0.00626 0.0151 1.0000 1.0000
2.500 0.1758 0.01602 0.00674 0.0165 1.0000 1.0000
3.000 0.3428 0.02029 0.00833 0.0021 0.2061 1.0000
3.250 0.3696 0.02137 0.00939 0.0028 0.1933 1.0000
3.500 0.3984 0.02261 0.01059 0.0033 0.1849 1.0000
3.750 0.4272 0.02386 0.01208 0.0040 0.1779 1.0000
4.000 0.4534 0.02526 0.01353 0.0048 0.1682 1.0000
4.250 0.4805 0.02694 0.01551 0.0056 0.1641 1.0000
4.500 0.5071 0.02899 0.01790 0.0065 0.1624 1.0000
4.750 0.5319 0.03125 0.02033 0.0073 0.1584 1.0000
5.000 0.5551 0.03376 0.02343 0.0084 0.1543 1.0000
5.250 0.5781 0.03702 0.02711 0.0093 0.1563 1.0000
5.500 0.5991 0.04052 0.03105 0.0102 0.1570 1.0000
5.750 0.6180 0.04419 0.03537 0.0110 0.1590 1.0000
6.000 0.6340 0.05028 0.04237 0.0100 0.1813 1.0000
7.000 0.5763 0.08083 0.07391 -0.0335 0.4773 1.0000
7.250 0.5954 0.08458 0.07768 -0.0310 0.4393 1.0000
7.500 0.6154 0.08890 0.08204 -0.0294 0.4141 1.0000
7.750 0.6047 0.09101 0.08408 -0.0284 0.3919 1.0000
8.000 0.6344 0.09663 0.08977 -0.0267 0.3708 1.0000
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Polar data table (+)
Polar graphs
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