EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 100,000 Max Cl/Cd: 23.38 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea81006-il-100000-n5.txt Download as CSV file: xf-ea81006-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6869 0.08406 0.07922 -0.0044 1.0000 0.0221
-9.000 -0.6946 0.07815 0.07336 -0.0092 1.0000 0.0219
-8.750 -0.7048 0.07282 0.06801 -0.0121 1.0000 0.0218
-8.500 -0.7135 0.06722 0.06232 -0.0142 1.0000 0.0217
-8.250 -0.7203 0.06143 0.05637 -0.0156 1.0000 0.0217
-8.000 -0.7245 0.05573 0.05040 -0.0162 1.0000 0.0217
-7.750 -0.7265 0.04977 0.04404 -0.0159 1.0000 0.0219
-7.500 -0.7163 0.04694 0.04100 -0.0153 1.0000 0.0230
-7.250 -0.7064 0.04338 0.03706 -0.0145 1.0000 0.0250
-7.000 -0.6947 0.03990 0.03306 -0.0134 1.0000 0.0270
-6.750 -0.6810 0.03632 0.02896 -0.0120 1.0000 0.0287
-6.500 -0.6649 0.03312 0.02524 -0.0106 1.0000 0.0308
-6.250 -0.6462 0.03073 0.02234 -0.0093 1.0000 0.0345
-6.000 -0.6256 0.02950 0.02081 -0.0083 1.0000 0.0401
-5.750 -0.6047 0.02753 0.01821 -0.0069 1.0000 0.0454
-5.500 -0.5834 0.02603 0.01664 -0.0063 1.0000 0.0514
-5.250 -0.5611 0.02455 0.01477 -0.0053 1.0000 0.0575
-5.000 -0.5376 0.02327 0.01317 -0.0043 1.0000 0.0618
-4.750 -0.5141 0.02199 0.01183 -0.0037 1.0000 0.0664
-4.500 -0.4897 0.02095 0.01053 -0.0028 1.0000 0.0683
-4.250 -0.4655 0.01995 0.00945 -0.0020 1.0000 0.0699
-4.000 -0.4423 0.01897 0.00853 -0.0012 1.0000 0.0726
-3.750 -0.4191 0.01822 0.00774 -0.0003 1.0000 0.0744
-3.500 -0.3963 0.01755 0.00704 0.0008 1.0000 0.0756
-3.250 -0.3746 0.01683 0.00633 0.0019 1.0000 0.0771
-3.000 -0.3530 0.01622 0.00575 0.0030 1.0000 0.0794
-2.750 -0.3309 0.01574 0.00524 0.0041 1.0000 0.0816
-2.500 -0.3085 0.01534 0.00479 0.0052 1.0000 0.0831
-2.250 -0.2864 0.01490 0.00435 0.0063 1.0000 0.0851
-2.000 -0.2641 0.01453 0.00396 0.0073 1.0000 0.0887
-1.750 -0.2416 0.01423 0.00366 0.0083 1.0000 0.0931
-1.500 -0.2192 0.01391 0.00341 0.0094 1.0000 0.0991
-1.250 -0.1976 0.01343 0.00324 0.0104 1.0000 0.1328
-1.000 -0.1768 0.01267 0.00311 0.0114 1.0000 0.2887
-0.750 -0.1612 0.01125 0.00311 0.0135 1.0000 0.6051
-0.500 -0.1327 0.01078 0.00354 0.0150 1.0000 0.8629
-0.250 -0.0644 0.01088 0.00374 0.0075 1.0000 0.9635
0.250 0.0642 0.01088 0.00374 -0.0075 0.9638 1.0000
0.500 0.1330 0.01078 0.00353 -0.0150 0.8620 1.0000
0.750 0.1613 0.01123 0.00312 -0.0135 0.6087 1.0000
1.000 0.1769 0.01266 0.00311 -0.0113 0.2909 1.0000
1.250 0.1975 0.01344 0.00324 -0.0104 0.1307 1.0000
1.500 0.2192 0.01391 0.00341 -0.0093 0.0991 1.0000
1.750 0.2416 0.01423 0.00366 -0.0083 0.0931 1.0000
2.000 0.2641 0.01453 0.00396 -0.0073 0.0887 1.0000
2.250 0.2864 0.01490 0.00435 -0.0062 0.0851 1.0000
2.500 0.3085 0.01534 0.00479 -0.0052 0.0831 1.0000
2.750 0.3309 0.01574 0.00524 -0.0041 0.0815 1.0000
3.000 0.3530 0.01621 0.00574 -0.0030 0.0795 1.0000
3.250 0.3746 0.01683 0.00633 -0.0019 0.0771 1.0000
3.500 0.3963 0.01755 0.00703 -0.0008 0.0755 1.0000
3.750 0.4191 0.01821 0.00773 0.0003 0.0745 1.0000
4.000 0.4423 0.01897 0.00853 0.0012 0.0727 1.0000
4.250 0.4655 0.01994 0.00944 0.0020 0.0700 1.0000
4.500 0.4896 0.02094 0.01053 0.0029 0.0683 1.0000
4.750 0.5140 0.02199 0.01183 0.0037 0.0665 1.0000
5.000 0.5375 0.02326 0.01317 0.0044 0.0618 1.0000
5.250 0.5610 0.02455 0.01477 0.0053 0.0575 1.0000
5.500 0.5833 0.02602 0.01663 0.0063 0.0514 1.0000
5.750 0.6046 0.02754 0.01822 0.0069 0.0454 1.0000
6.000 0.6256 0.02950 0.02082 0.0083 0.0401 1.0000
6.250 0.6461 0.03074 0.02235 0.0093 0.0345 1.0000
6.500 0.6648 0.03310 0.02522 0.0106 0.0308 1.0000
6.750 0.6809 0.03633 0.02898 0.0121 0.0287 1.0000
7.000 0.6946 0.03990 0.03306 0.0134 0.0270 1.0000
7.250 0.7063 0.04339 0.03708 0.0145 0.0249 1.0000
7.500 0.7161 0.04699 0.04106 0.0154 0.0230 1.0000
7.750 0.7262 0.04982 0.04410 0.0159 0.0219 1.0000
8.000 0.7247 0.05564 0.05031 0.0162 0.0217 1.0000
8.250 0.7199 0.06155 0.05649 0.0156 0.0216 1.0000
8.500 0.7138 0.06715 0.06225 0.0142 0.0217 1.0000
8.750 0.7045 0.07294 0.06813 0.0120 0.0218 1.0000
9.000 0.6947 0.07819 0.07339 0.0091 0.0219 1.0000
9.250 0.6871 0.08410 0.07926 0.0043 0.0221 1.0000
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Polar data table (+)
Polar graphs
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