E71 (5.15%) (e71-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 100,000 Max Cl/Cd: 75.06 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e71-il-100000.txt Download as CSV file: xf-e71-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3773 0.09922 0.09463 -0.0195 1.0000 0.0597
-6.750 -0.3841 0.09782 0.09331 -0.0181 1.0000 0.0609
-6.500 -0.3892 0.09663 0.09222 -0.0196 1.0000 0.0625
-6.250 -0.3871 0.09548 0.09115 -0.0258 1.0000 0.0634
-6.000 -0.3736 0.09321 0.08889 -0.0349 1.0000 0.0638
-5.750 -0.3822 0.08757 0.08333 -0.0221 1.0000 0.0657
-5.500 -0.3782 0.08466 0.08045 -0.0199 1.0000 0.0681
-5.250 -0.3717 0.08185 0.07767 -0.0209 1.0000 0.0710
-5.000 -0.3572 0.07880 0.07459 -0.0265 1.0000 0.0752
-4.750 -0.3265 0.07403 0.06977 -0.0395 1.0000 0.0781
-4.500 -0.3271 0.07113 0.06692 -0.0341 1.0000 0.0801
-4.250 -0.2622 0.06633 0.06179 -0.0560 1.0000 0.0910
-4.000 -0.2691 0.06266 0.05831 -0.0488 1.0000 0.0925
-3.750 -0.2452 0.05972 0.05531 -0.0519 1.0000 0.1033
-3.500 -0.2291 0.05614 0.05175 -0.0526 1.0000 0.1096
-3.250 -0.1894 0.05188 0.04735 -0.0604 1.0000 0.1220
-3.000 -0.1525 0.04817 0.04351 -0.0663 1.0000 0.1362
-2.750 -0.1013 0.04437 0.03939 -0.0757 1.0000 0.1612
-2.500 -0.0736 0.04155 0.03655 -0.0776 1.0000 0.1770
-2.250 -0.0362 0.03887 0.03374 -0.0819 1.0000 0.2042
-2.000 0.1096 0.02646 0.01912 -0.1062 1.0000 0.0711
-1.750 0.1534 0.02413 0.01616 -0.1094 1.0000 0.0688
-1.500 0.1900 0.02262 0.01424 -0.1111 1.0000 0.0698
-1.250 0.2246 0.02135 0.01258 -0.1122 1.0000 0.0689
-1.000 0.2557 0.02049 0.01161 -0.1128 1.0000 0.0706
-0.750 0.2859 0.01989 0.01094 -0.1134 1.0000 0.0753
-0.500 0.3178 0.01937 0.01043 -0.1144 1.0000 0.0892
-0.250 0.3510 0.01660 0.01020 -0.1148 1.0000 0.9059
0.000 0.3711 0.01699 0.01027 -0.1140 1.0000 1.0000
0.250 0.3942 0.01748 0.01052 -0.1137 1.0000 1.0000
0.500 0.4166 0.01801 0.01086 -0.1134 1.0000 1.0000
0.750 0.4385 0.01858 0.01130 -0.1131 1.0000 1.0000
1.000 0.4599 0.01919 0.01181 -0.1128 1.0000 1.0000
1.250 0.4894 0.01989 0.01242 -0.1142 0.9962 1.0000
1.500 0.5345 0.02057 0.01301 -0.1183 0.9857 1.0000
1.750 0.5782 0.02110 0.01350 -0.1220 0.9745 1.0000
2.000 0.6216 0.02148 0.01389 -0.1255 0.9629 1.0000
2.250 0.6654 0.02172 0.01418 -0.1288 0.9509 1.0000
2.500 0.7094 0.02182 0.01433 -0.1320 0.9386 1.0000
2.750 0.7542 0.02173 0.01434 -0.1351 0.9256 1.0000
3.000 0.8002 0.02144 0.01418 -0.1381 0.9119 1.0000
3.250 0.8466 0.02096 0.01393 -0.1408 0.8979 1.0000
3.500 0.8945 0.02022 0.01341 -0.1435 0.8834 1.0000
3.750 0.9453 0.01909 0.01254 -0.1461 0.8684 1.0000
4.000 1.0007 0.01760 0.01143 -0.1491 0.8516 1.0000
4.250 1.0458 0.01638 0.01050 -0.1500 0.8245 1.0000
4.500 1.0854 0.01548 0.00982 -0.1500 0.7821 1.0000
4.750 1.1224 0.01498 0.00938 -0.1495 0.7128 1.0000
5.000 1.1499 0.01532 0.00934 -0.1474 0.5858 1.0000
5.250 1.1579 0.01712 0.00989 -0.1428 0.3954 1.0000
5.500 1.1640 0.01944 0.01099 -0.1392 0.2241 1.0000
5.750 1.1677 0.02333 0.01352 -0.1352 0.0681 1.0000
6.000 1.1802 0.02605 0.01609 -0.1320 0.0496 1.0000
6.250 1.2003 0.02806 0.01824 -0.1300 0.0430 1.0000
6.500 1.2220 0.03084 0.02097 -0.1289 0.0374 1.0000
6.750 1.2486 0.03315 0.02355 -0.1279 0.0345 1.0000
7.000 1.2766 0.03637 0.02717 -0.1271 0.0336 1.0000
7.250 1.3017 0.04011 0.03137 -0.1257 0.0338 1.0000
7.500 1.3217 0.04429 0.03611 -0.1237 0.0347 1.0000
7.750 1.3369 0.04894 0.04130 -0.1213 0.0359 1.0000
8.000 1.3476 0.05428 0.04709 -0.1190 0.0372 1.0000
8.250 1.3571 0.05868 0.05230 -0.1151 0.0414 1.0000
8.500 1.3530 0.06590 0.06021 -0.1111 0.0467 1.0000
8.750 1.3523 0.07574 0.07054 -0.1083 0.0611 1.0000
9.000 1.2635 0.07708 0.07265 -0.0954 0.0612 1.0000
9.250 1.2268 0.08051 0.07644 -0.0900 0.0599 1.0000
9.500 1.1975 0.08513 0.08126 -0.0868 0.0597 1.0000
9.750 1.1696 0.09081 0.08711 -0.0854 0.0601 1.0000
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Polar data table (+)
Polar graphs
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