EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 500,000 Max Cl/Cd: 60.68 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e874-il-500000-n5.txt Download as CSV file: xf-e874-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 874 HYDROFOIL 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6109 0.08498 0.08281 -0.0080 1.0000 0.0036
-9.250 -0.6204 0.07874 0.07661 -0.0113 1.0000 0.0036
-9.000 -0.6315 0.07225 0.07016 -0.0153 1.0000 0.0035
-8.750 -0.6480 0.06463 0.06259 -0.0219 1.0000 0.0035
-8.250 -0.6785 0.04778 0.04541 -0.0288 1.0000 0.0033
-8.000 -0.6885 0.04200 0.03934 -0.0278 1.0000 0.0033
-7.750 -0.6945 0.03656 0.03351 -0.0257 1.0000 0.0032
-7.500 -0.6942 0.03197 0.02850 -0.0231 1.0000 0.0032
-7.250 -0.6894 0.02795 0.02402 -0.0202 1.0000 0.0031
-7.000 -0.6800 0.02465 0.02028 -0.0175 1.0000 0.0032
-6.750 -0.6663 0.02212 0.01737 -0.0151 1.0000 0.0034
-6.500 -0.6502 0.02006 0.01498 -0.0130 1.0000 0.0036
-6.250 -0.6320 0.01845 0.01310 -0.0112 1.0000 0.0037
-6.000 -0.6126 0.01711 0.01153 -0.0095 1.0000 0.0040
-5.750 -0.5920 0.01611 0.01036 -0.0080 1.0000 0.0042
-5.500 -0.5704 0.01540 0.00948 -0.0067 1.0000 0.0044
-5.250 -0.5527 0.01388 0.00780 -0.0049 1.0000 0.0051
-5.000 -0.5320 0.01305 0.00686 -0.0034 1.0000 0.0053
-4.750 -0.5045 0.01222 0.00590 -0.0034 0.9986 0.0053
-4.500 -0.4707 0.01151 0.00507 -0.0047 0.9956 0.0054
-4.250 -0.4382 0.01094 0.00439 -0.0058 0.9921 0.0055
-4.000 -0.4057 0.01046 0.00380 -0.0068 0.9873 0.0058
-3.750 -0.3740 0.01008 0.00330 -0.0076 0.9816 0.0062
-3.000 -0.2876 0.00845 0.00210 -0.0085 0.9451 0.1263
-2.750 -0.2425 0.00808 0.00186 -0.0125 0.9291 0.1694
-2.500 -0.1899 0.00763 0.00160 -0.0182 0.9025 0.2353
-2.250 -0.1498 0.00745 0.00140 -0.0210 0.8565 0.2741
-2.000 -0.1232 0.00743 0.00128 -0.0206 0.8096 0.3040
-1.750 -0.0992 0.00743 0.00117 -0.0197 0.7682 0.3331
-1.500 -0.0752 0.00740 0.00109 -0.0189 0.7329 0.3663
-1.250 -0.0511 0.00735 0.00103 -0.0180 0.7023 0.4016
-1.000 -0.0268 0.00728 0.00098 -0.0173 0.6757 0.4413
-0.750 -0.0027 0.00719 0.00094 -0.0165 0.6518 0.4874
-0.500 0.0210 0.00706 0.00091 -0.0156 0.6299 0.5442
-0.250 0.0443 0.00691 0.00090 -0.0147 0.6092 0.6043
0.000 0.0670 0.00675 0.00089 -0.0135 0.5897 0.6693
0.250 0.0885 0.00652 0.00090 -0.0121 0.5723 0.7519
0.500 0.1146 0.00624 0.00095 -0.0114 0.5565 0.8574
1.000 0.2414 0.00653 0.00128 -0.0271 0.5193 0.9624
1.250 0.2698 0.00667 0.00138 -0.0272 0.5065 0.9779
1.500 0.3027 0.00680 0.00149 -0.0283 0.4944 0.9864
1.750 0.3400 0.00691 0.00158 -0.0305 0.4821 0.9926
2.000 0.3790 0.00700 0.00166 -0.0330 0.4691 0.9971
2.500 0.4387 0.00723 0.00183 -0.0340 0.4294 1.0000
2.750 0.4605 0.00761 0.00188 -0.0329 0.3514 1.0000
3.000 0.4782 0.00859 0.00214 -0.0314 0.1784 1.0000
3.250 0.4970 0.00957 0.00258 -0.0300 0.0513 1.0000
3.500 0.5188 0.01012 0.00296 -0.0288 0.0108 1.0000
3.750 0.5425 0.01042 0.00336 -0.0278 0.0081 1.0000
4.000 0.5657 0.01076 0.00374 -0.0269 0.0062 1.0000
4.250 0.5881 0.01123 0.00429 -0.0257 0.0050 1.0000
4.500 0.6107 0.01168 0.00483 -0.0246 0.0046 1.0000
4.750 0.6324 0.01224 0.00548 -0.0233 0.0041 1.0000
5.000 0.6531 0.01293 0.00626 -0.0219 0.0037 1.0000
5.250 0.6732 0.01370 0.00713 -0.0203 0.0035 1.0000
5.500 0.6926 0.01459 0.00815 -0.0186 0.0033 1.0000
5.750 0.7117 0.01560 0.00929 -0.0168 0.0033 1.0000
6.000 0.7304 0.01680 0.01062 -0.0150 0.0032 1.0000
6.250 0.7491 0.01822 0.01221 -0.0131 0.0032 1.0000
6.500 0.7676 0.01993 0.01414 -0.0112 0.0032 1.0000
6.750 0.7852 0.02209 0.01657 -0.0090 0.0033 1.0000
7.000 0.8004 0.02501 0.01987 -0.0065 0.0034 1.0000
7.250 0.8126 0.02851 0.02378 -0.0035 0.0036 1.0000
7.500 0.8223 0.03201 0.02766 -0.0006 0.0038 1.0000
7.750 0.8293 0.03558 0.03157 0.0023 0.0040 1.0000
8.000 0.8327 0.03933 0.03564 0.0051 0.0042 1.0000
8.250 0.8341 0.04286 0.03944 0.0078 0.0044 1.0000
8.500 0.8315 0.04652 0.04334 0.0103 0.0045 1.0000
8.750 0.8218 0.05047 0.04752 0.0129 0.0047 1.0000
9.000 0.8087 0.05408 0.05130 0.0152 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 874 HYDROFOIL AIRFOIL (e874-il)