E71 (5.15%) (e71-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 50,000 Max Cl/Cd: 48.52 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e71-il-50000.txt Download as CSV file: xf-e71-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3735 0.11241 0.10563 -0.0229 1.0000 0.1274
-7.750 -0.3815 0.11187 0.10521 -0.0227 1.0000 0.1308
-7.500 -0.3962 0.11230 0.10579 -0.0221 1.0000 0.1319
-7.250 -0.3752 0.10556 0.09903 -0.0205 1.0000 0.1395
-7.000 -0.3850 0.10485 0.09844 -0.0194 1.0000 0.1440
-6.750 -0.3956 0.10489 0.09864 -0.0211 1.0000 0.1457
-6.500 -0.3826 0.09936 0.09311 -0.0173 1.0000 0.1549
-6.250 -0.3898 0.09895 0.09283 -0.0202 1.0000 0.1593
-6.000 -0.3814 0.09442 0.08833 -0.0167 1.0000 0.1654
-5.750 -0.3830 0.09345 0.08747 -0.0208 1.0000 0.1732
-5.500 -0.3766 0.08921 0.08322 -0.0170 1.0000 0.1793
-5.250 -0.3718 0.08769 0.08177 -0.0233 1.0000 0.1881
-5.000 -0.3665 0.08379 0.07791 -0.0181 1.0000 0.1963
-4.750 -0.3594 0.08084 0.07501 -0.0197 1.0000 0.2055
-4.500 -0.3495 0.07796 0.07217 -0.0221 1.0000 0.2178
-4.250 -0.3388 0.07494 0.06917 -0.0232 1.0000 0.2316
-4.000 -0.3282 0.07183 0.06610 -0.0233 1.0000 0.2467
-3.750 -0.3163 0.06884 0.06313 -0.0234 1.0000 0.2642
-3.500 -0.3005 0.06575 0.06006 -0.0255 1.0000 0.2876
-3.250 -0.2847 0.06285 0.05716 -0.0266 1.0000 0.3142
-3.000 -0.2723 0.06000 0.05435 -0.0256 1.0000 0.3426
-2.750 -0.2591 0.05741 0.05178 -0.0247 1.0000 0.3826
-2.500 -0.2555 0.05500 0.04940 -0.0196 1.0000 0.4252
-2.250 0.0321 0.03650 0.02815 -0.0972 1.0000 0.1463
-2.000 0.0848 0.03246 0.02351 -0.1029 1.0000 0.1281
-1.750 0.1384 0.02946 0.01943 -0.1080 1.0000 0.1184
-1.500 0.1758 0.02750 0.01701 -0.1098 1.0000 0.1182
-1.250 0.2094 0.02592 0.01516 -0.1110 1.0000 0.1224
-1.000 0.2404 0.02492 0.01399 -0.1115 1.0000 0.1386
-0.750 0.2711 0.02394 0.01290 -0.1118 1.0000 0.1680
-0.500 0.2978 0.01981 0.01160 -0.1098 1.0000 0.9158
-0.250 0.3233 0.02012 0.01104 -0.1095 1.0000 1.0000
0.000 0.3484 0.02053 0.01100 -0.1095 1.0000 1.0000
0.250 0.3725 0.02098 0.01108 -0.1093 1.0000 1.0000
0.500 0.3961 0.02146 0.01131 -0.1092 1.0000 1.0000
0.750 0.4190 0.02199 0.01163 -0.1090 1.0000 1.0000
1.000 0.4415 0.02256 0.01204 -0.1088 1.0000 1.0000
1.250 0.4634 0.02317 0.01253 -0.1086 1.0000 1.0000
1.500 0.4850 0.02383 0.01310 -0.1084 1.0000 1.0000
1.750 0.5059 0.02454 0.01375 -0.1082 1.0000 1.0000
2.000 0.5262 0.02532 0.01449 -0.1080 1.0000 1.0000
2.250 0.5460 0.02616 0.01532 -0.1078 1.0000 1.0000
2.500 0.5652 0.02707 0.01625 -0.1076 1.0000 1.0000
2.750 0.5838 0.02807 0.01729 -0.1075 1.0000 1.0000
3.000 0.6017 0.02916 0.01848 -0.1074 1.0000 1.0000
3.250 0.6188 0.03036 0.01976 -0.1074 1.0000 1.0000
3.500 0.6351 0.03168 0.02117 -0.1074 1.0000 1.0000
3.750 0.6720 0.03334 0.02301 -0.1115 0.9868 1.0000
4.000 0.7344 0.03471 0.02474 -0.1193 0.9593 1.0000
4.250 0.7941 0.03538 0.02575 -0.1257 0.9298 1.0000
4.500 0.8533 0.03542 0.02618 -0.1309 0.8979 1.0000
4.750 0.9254 0.03435 0.02577 -0.1366 0.8649 1.0000
5.000 0.9987 0.03186 0.02398 -0.1401 0.8256 1.0000
5.250 1.0783 0.02740 0.02039 -0.1413 0.7734 1.0000
5.500 1.1375 0.02356 0.01714 -0.1380 0.6721 1.0000
5.750 1.1596 0.02390 0.01640 -0.1315 0.4733 1.0000
6.000 1.1621 0.02727 0.01822 -0.1260 0.3048 1.0000
6.250 1.1693 0.03139 0.02109 -0.1222 0.1715 1.0000
6.500 1.1914 0.03535 0.02445 -0.1205 0.1059 1.0000
6.750 1.2225 0.03894 0.02797 -0.1201 0.0845 1.0000
7.000 1.2548 0.04291 0.03203 -0.1200 0.0755 1.0000
7.250 1.2818 0.04728 0.03699 -0.1187 0.0732 1.0000
7.500 1.3024 0.05178 0.04225 -0.1167 0.0726 1.0000
7.750 1.3182 0.05665 0.04770 -0.1145 0.0731 1.0000
8.000 1.3313 0.06192 0.05343 -0.1124 0.0741 1.0000
8.250 1.3426 0.06777 0.05962 -0.1106 0.0749 1.0000
8.500 1.3279 0.07222 0.06534 -0.1054 0.0798 1.0000
8.750 1.3200 0.07800 0.07161 -0.1027 0.0828 1.0000
9.000 1.3139 0.08360 0.07750 -0.1006 0.0850 1.0000
9.250 1.3160 0.08976 0.08377 -0.0995 0.0870 1.0000
9.500 1.1984 0.09050 0.08525 -0.0851 0.0884 1.0000
9.750 1.1538 0.09534 0.09035 -0.0829 0.0892 1.0000
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Polar data table (+)
Polar graphs
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