EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 500,000 Max Cl/Cd: 53.48 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea81006-il-500000-n5.txt Download as CSV file: xf-ea81006-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7519 0.08512 0.08291 0.0013 1.0000 0.0052
-10.250 -0.7767 0.07580 0.07365 -0.0052 1.0000 0.0052
-10.000 -0.8033 0.06675 0.06461 -0.0140 1.0000 0.0051
-9.750 -0.8400 0.05718 0.05490 -0.0172 1.0000 0.0050
-9.500 -0.8854 0.04298 0.04015 -0.0180 1.0000 0.0048
-9.250 -0.9040 0.03325 0.02977 -0.0157 1.0000 0.0048
-9.000 -0.9007 0.02782 0.02376 -0.0137 1.0000 0.0050
-8.750 -0.8878 0.02474 0.02028 -0.0122 1.0000 0.0051
-8.500 -0.8709 0.02254 0.01774 -0.0110 1.0000 0.0052
-8.250 -0.8538 0.02035 0.01521 -0.0097 1.0000 0.0054
-8.000 -0.8358 0.01832 0.01283 -0.0083 1.0000 0.0058
-7.750 -0.8146 0.01713 0.01145 -0.0074 1.0000 0.0064
-7.500 -0.7923 0.01622 0.01039 -0.0065 1.0000 0.0069
-7.250 -0.7696 0.01541 0.00945 -0.0057 1.0000 0.0075
-7.000 -0.7466 0.01468 0.00858 -0.0049 1.0000 0.0081
-6.750 -0.7235 0.01405 0.00785 -0.0041 1.0000 0.0090
-6.500 -0.7003 0.01351 0.00721 -0.0033 1.0000 0.0097
-6.250 -0.6775 0.01280 0.00639 -0.0022 1.0000 0.0125
-6.000 -0.6547 0.01224 0.00576 -0.0013 1.0000 0.0158
-5.750 -0.6306 0.01200 0.00561 -0.0006 1.0000 0.0233
-5.500 -0.6057 0.01195 0.00554 0.0000 1.0000 0.0300
-5.250 -0.5802 0.01203 0.00557 0.0005 1.0000 0.0334
-5.000 -0.5551 0.01208 0.00560 0.0010 1.0000 0.0350
-4.750 -0.5304 0.01212 0.00559 0.0017 1.0000 0.0372
-4.500 -0.5061 0.01214 0.00557 0.0024 1.0000 0.0394
-4.250 -0.4821 0.01222 0.00563 0.0031 1.0000 0.0414
-4.000 -0.4594 0.01193 0.00530 0.0041 1.0000 0.0425
-3.750 -0.4372 0.01158 0.00492 0.0052 1.0000 0.0432
-3.500 -0.4059 0.01123 0.00455 0.0043 0.9977 0.0440
-3.250 -0.3666 0.01091 0.00419 0.0017 0.9915 0.0447
-3.000 -0.3300 0.01034 0.00363 -0.0004 0.9847 0.0460
-2.750 -0.2963 0.00992 0.00322 -0.0018 0.9775 0.0472
-2.500 -0.2604 0.00959 0.00290 -0.0036 0.9681 0.0482
-2.250 -0.2238 0.00930 0.00260 -0.0055 0.9508 0.0493
-2.000 -0.1889 0.00908 0.00232 -0.0068 0.9137 0.0504
-1.750 -0.1630 0.00899 0.00210 -0.0061 0.8645 0.0517
-1.500 -0.1404 0.00904 0.00189 -0.0047 0.7922 0.0529
-1.250 -0.1249 0.00993 0.00174 -0.0021 0.5080 0.0536
-1.000 -0.1045 0.01089 0.00172 -0.0012 0.2047 0.0544
-0.750 -0.0798 0.01124 0.00168 -0.0008 0.0688 0.0551
-0.500 -0.0533 0.01118 0.00161 -0.0005 0.0643 0.0563
-0.250 -0.0267 0.01114 0.00156 -0.0002 0.0618 0.0582
0.000 0.0000 0.01112 0.00154 0.0000 0.0601 0.0601
0.250 0.0267 0.01114 0.00156 0.0002 0.0582 0.0619
0.500 0.0532 0.01119 0.00161 0.0005 0.0563 0.0643
0.750 0.0797 0.01124 0.00168 0.0008 0.0551 0.0688
1.000 0.1045 0.01089 0.00172 0.0012 0.0544 0.2029
1.250 0.1249 0.00993 0.00175 0.0021 0.0536 0.5072
1.500 0.1404 0.00904 0.00189 0.0047 0.0528 0.7909
1.750 0.1629 0.00899 0.00210 0.0061 0.0517 0.8645
2.000 0.1889 0.00907 0.00232 0.0069 0.0504 0.9146
2.250 0.2237 0.00930 0.00260 0.0055 0.0493 0.9507
2.500 0.2604 0.00959 0.00290 0.0036 0.0482 0.9682
2.750 0.2963 0.00992 0.00322 0.0018 0.0471 0.9777
3.000 0.3299 0.01034 0.00363 0.0004 0.0460 0.9848
3.250 0.3666 0.01091 0.00419 -0.0017 0.0447 0.9915
3.500 0.4060 0.01123 0.00455 -0.0043 0.0440 0.9977
3.750 0.4371 0.01158 0.00493 -0.0052 0.0433 1.0000
4.000 0.4593 0.01193 0.00530 -0.0041 0.0425 1.0000
4.250 0.4820 0.01222 0.00562 -0.0031 0.0414 1.0000
4.750 0.5302 0.01214 0.00561 -0.0016 0.0373 1.0000
5.000 0.5549 0.01210 0.00561 -0.0010 0.0351 1.0000
5.250 0.5800 0.01203 0.00557 -0.0004 0.0334 1.0000
5.500 0.6055 0.01196 0.00554 0.0001 0.0300 1.0000
5.750 0.6304 0.01201 0.00563 0.0007 0.0235 1.0000
6.000 0.6546 0.01224 0.00576 0.0013 0.0158 1.0000
6.250 0.6774 0.01281 0.00640 0.0023 0.0124 1.0000
6.500 0.7002 0.01350 0.00720 0.0033 0.0097 1.0000
6.750 0.7234 0.01406 0.00785 0.0041 0.0090 1.0000
7.000 0.7465 0.01468 0.00858 0.0049 0.0082 1.0000
7.250 0.7694 0.01542 0.00946 0.0058 0.0075 1.0000
7.500 0.7922 0.01621 0.01039 0.0066 0.0069 1.0000
7.750 0.8145 0.01713 0.01145 0.0074 0.0064 1.0000
8.000 0.8359 0.01828 0.01279 0.0083 0.0059 1.0000
8.250 0.8538 0.02032 0.01516 0.0097 0.0054 1.0000
8.500 0.8708 0.02256 0.01777 0.0110 0.0052 1.0000
8.750 0.8878 0.02472 0.02025 0.0123 0.0051 1.0000
9.000 0.9007 0.02781 0.02375 0.0137 0.0050 1.0000
9.250 0.9062 0.03268 0.02915 0.0156 0.0048 1.0000
9.500 0.8903 0.04188 0.03900 0.0178 0.0048 1.0000
9.750 0.8402 0.05717 0.05489 0.0172 0.0050 1.0000
10.000 0.8053 0.06644 0.06431 0.0141 0.0051 1.0000
10.250 0.7764 0.07598 0.07382 0.0050 0.0052 1.0000
10.500 0.7024 0.07126 0.06923 0.0035 0.0054 1.0000
10.750 0.6843 0.07937 0.07731 -0.0003 0.0055 1.0000
11.000 0.6601 0.08917 0.08709 -0.0046 0.0055 1.0000
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Polar data table (+)
Polar graphs
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