E64 (8.45%) (e64-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E64 (8.45%) (e64-il) Reynolds number: 500,000 Max Cl/Cd: 120.58 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e64-il-500000.txt Download as CSV file: xf-e64-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3204 0.08827 0.08622 -0.0300 1.0000 0.0181
-8.750 -0.3289 0.08482 0.08280 -0.0303 1.0000 0.0188
-8.500 -0.3356 0.08195 0.07997 -0.0298 1.0000 0.0190
-8.250 -0.3351 0.07758 0.07561 -0.0323 0.9991 0.0191
-8.000 -0.3295 0.07224 0.07028 -0.0363 0.9972 0.0192
-7.750 -0.3351 0.06422 0.06228 -0.0407 0.9952 0.0197
-7.500 -0.3258 0.06068 0.05874 -0.0427 0.9925 0.0202
-7.250 -0.3173 0.05652 0.05458 -0.0462 0.9888 0.0206
-7.000 -0.3049 0.05118 0.04924 -0.0528 0.9855 0.0211
-6.750 -0.2937 0.04520 0.04325 -0.0612 0.9799 0.0216
-6.500 -0.2763 0.03720 0.03517 -0.0731 0.9756 0.0222
-6.250 -0.2531 0.02883 0.02658 -0.0840 0.9731 0.0235
-6.000 -0.2289 0.02373 0.02103 -0.0894 0.9674 0.0261
-5.750 -0.2113 0.01546 0.01222 -0.0956 0.9634 0.0275
-5.500 -0.1814 0.01317 0.00990 -0.0981 0.9617 0.0288
-5.250 -0.1485 0.01092 0.00742 -0.1010 0.9603 0.0313
-5.000 -0.1077 0.01108 0.00720 -0.1029 0.9593 0.0356
-4.750 -0.1122 0.01612 0.01086 -0.1033 0.9606 0.0160
-4.500 -0.0756 0.01399 0.00837 -0.1048 0.9596 0.0150
-4.250 -0.0487 0.01298 0.00726 -0.1046 0.9546 0.0155
-4.000 -0.0154 0.01211 0.00631 -0.1058 0.9517 0.0161
-3.750 0.0205 0.01147 0.00561 -0.1075 0.9499 0.0175
-3.500 0.0577 0.01081 0.00489 -0.1095 0.9484 0.0185
-3.250 0.0950 0.01018 0.00418 -0.1114 0.9470 0.0191
-3.000 0.1295 0.00953 0.00345 -0.1127 0.9443 0.0224
-2.750 0.1586 0.00899 0.00299 -0.1129 0.9386 0.0506
-2.500 0.1924 0.00816 0.00268 -0.1145 0.9352 0.1885
-2.250 0.2274 0.00762 0.00247 -0.1163 0.9324 0.2941
-2.000 0.2546 0.00727 0.00235 -0.1162 0.9252 0.3781
-1.750 0.2865 0.00682 0.00224 -0.1172 0.9202 0.4886
-1.500 0.3155 0.00654 0.00216 -0.1174 0.9135 0.5684
-1.250 0.3446 0.00628 0.00209 -0.1175 0.9064 0.6432
-1.000 0.3723 0.00610 0.00204 -0.1172 0.8981 0.7016
-0.750 0.4006 0.00592 0.00198 -0.1170 0.8902 0.7593
-0.500 0.4249 0.00579 0.00198 -0.1159 0.8799 0.8132
-0.250 0.4488 0.00567 0.00195 -0.1146 0.8700 0.8638
0.000 0.4711 0.00557 0.00189 -0.1129 0.8597 0.9136
0.250 0.5005 0.00546 0.00179 -0.1128 0.8483 0.9713
0.500 0.5326 0.00546 0.00172 -0.1136 0.8357 1.0000
0.750 0.5602 0.00552 0.00170 -0.1135 0.8226 1.0000
1.000 0.5877 0.00558 0.00169 -0.1133 0.8088 1.0000
1.250 0.6148 0.00566 0.00170 -0.1131 0.7940 1.0000
1.500 0.6417 0.00575 0.00172 -0.1128 0.7780 1.0000
1.750 0.6683 0.00586 0.00175 -0.1124 0.7609 1.0000
2.000 0.6946 0.00596 0.00179 -0.1120 0.7422 1.0000
2.250 0.7207 0.00610 0.00185 -0.1115 0.7226 1.0000
2.500 0.7465 0.00625 0.00193 -0.1110 0.7018 1.0000
2.750 0.7719 0.00642 0.00202 -0.1104 0.6784 1.0000
3.000 0.7970 0.00661 0.00212 -0.1098 0.6528 1.0000
3.250 0.8216 0.00683 0.00224 -0.1091 0.6246 1.0000
3.500 0.8461 0.00708 0.00240 -0.1083 0.5954 1.0000
3.750 0.8702 0.00735 0.00256 -0.1076 0.5647 1.0000
4.000 0.8935 0.00768 0.00275 -0.1067 0.5273 1.0000
4.250 0.9151 0.00813 0.00297 -0.1055 0.4758 1.0000
4.500 0.9359 0.00868 0.00326 -0.1042 0.4169 1.0000
4.750 0.9573 0.00925 0.00356 -0.1032 0.3605 1.0000
5.000 0.9783 0.00988 0.00391 -0.1021 0.3026 1.0000
5.250 1.0001 0.01047 0.00428 -0.1011 0.2527 1.0000
5.500 1.0220 0.01106 0.00468 -0.1003 0.2091 1.0000
5.750 1.0438 0.01167 0.00510 -0.0994 0.1684 1.0000
6.000 1.0646 0.01240 0.00558 -0.0983 0.1234 1.0000
6.250 1.0843 0.01324 0.00615 -0.0971 0.0776 1.0000
6.500 1.1008 0.01445 0.00700 -0.0954 0.0259 1.0000
6.750 1.1221 0.01516 0.00770 -0.0942 0.0187 1.0000
7.000 1.1443 0.01573 0.00834 -0.0932 0.0170 1.0000
7.250 1.1655 0.01639 0.00906 -0.0921 0.0157 1.0000
7.500 1.1849 0.01724 0.00999 -0.0906 0.0146 1.0000
7.750 1.2008 0.01841 0.01131 -0.0886 0.0139 1.0000
8.000 1.2177 0.01944 0.01243 -0.0868 0.0136 1.0000
8.250 1.2355 0.02033 0.01342 -0.0852 0.0133 1.0000
8.500 1.2526 0.02129 0.01447 -0.0834 0.0129 1.0000
8.750 1.2688 0.02234 0.01563 -0.0816 0.0124 1.0000
9.000 1.2838 0.02357 0.01697 -0.0797 0.0123 1.0000
9.250 1.2983 0.02489 0.01839 -0.0777 0.0120 1.0000
9.500 1.3124 0.02630 0.01994 -0.0756 0.0118 1.0000
9.750 1.3265 0.02786 0.02165 -0.0736 0.0117 1.0000
10.000 1.3404 0.02957 0.02351 -0.0717 0.0115 1.0000
10.250 1.3537 0.03151 0.02562 -0.0698 0.0114 1.0000
10.500 1.3656 0.03383 0.02817 -0.0677 0.0114 1.0000
10.750 1.3740 0.03673 0.03136 -0.0653 0.0115 1.0000
11.000 1.3757 0.04011 0.03509 -0.0621 0.0118 1.0000
11.250 1.3720 0.04331 0.03859 -0.0586 0.0120 1.0000
11.500 1.3643 0.04652 0.04209 -0.0550 0.0120 1.0000
11.750 1.3534 0.04996 0.04580 -0.0518 0.0121 1.0000
12.000 1.3386 0.05390 0.05001 -0.0490 0.0123 1.0000
12.250 1.3197 0.05846 0.05483 -0.0469 0.0125 1.0000
12.500 1.2991 0.06345 0.06006 -0.0458 0.0128 1.0000
12.750 1.2763 0.06914 0.06596 -0.0458 0.0130 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E64 (8.45%) (e64-il)