E71 (5.15%) (e71-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 50,000 Max Cl/Cd: 49.48 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e71-il-50000-n5.txt Download as CSV file: xf-e71-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3772 0.10523 0.09863 -0.0229 1.0000 0.0850
-7.000 -0.3857 0.10441 0.09793 -0.0231 1.0000 0.0864
-6.750 -0.3892 0.10324 0.09690 -0.0263 1.0000 0.0871
-6.500 -0.3797 0.09782 0.09150 -0.0213 1.0000 0.0907
-6.250 -0.3772 0.09533 0.08906 -0.0208 1.0000 0.0961
-6.000 -0.3766 0.09387 0.08770 -0.0256 1.0000 0.1000
-5.750 -0.3726 0.09008 0.08398 -0.0233 1.0000 0.1038
-5.500 -0.3671 0.08734 0.08129 -0.0231 1.0000 0.1099
-5.000 -0.3509 0.08112 0.07516 -0.0277 1.0000 0.1180
-4.750 -0.3400 0.07804 0.07210 -0.0292 1.0000 0.1233
-4.500 -0.3194 0.07426 0.06831 -0.0365 1.0000 0.1297
-4.250 -0.3083 0.07099 0.06506 -0.0360 1.0000 0.1332
-3.750 -0.2093 0.05619 0.04967 -0.0617 1.0000 0.0627
-3.500 -0.1759 0.05176 0.04506 -0.0666 1.0000 0.0551
-3.250 -0.0966 0.04357 0.03595 -0.0832 1.0000 0.0468
-3.000 -0.0562 0.03955 0.03162 -0.0886 1.0000 0.0456
-2.750 -0.0085 0.03565 0.02720 -0.0950 1.0000 0.0444
-2.500 0.0394 0.03226 0.02306 -0.1004 1.0000 0.0437
-2.250 0.0827 0.02962 0.01977 -0.1043 1.0000 0.0436
-2.000 0.1195 0.02797 0.01742 -0.1063 1.0000 0.0470
-1.750 0.1513 0.02660 0.01592 -0.1079 1.0000 0.0534
-1.500 0.1830 0.02543 0.01438 -0.1087 1.0000 0.0568
-1.250 0.2132 0.02452 0.01309 -0.1090 1.0000 0.0600
-1.000 0.2436 0.02378 0.01212 -0.1096 1.0000 0.0659
-0.750 0.2748 0.02324 0.01140 -0.1105 1.0000 0.0779
-0.500 0.3117 0.02226 0.01087 -0.1128 1.0000 0.1891
-0.250 0.3210 0.02018 0.01111 -0.1092 1.0000 0.9528
0.000 0.3459 0.02056 0.01103 -0.1091 1.0000 1.0000
0.250 0.3702 0.02100 0.01110 -0.1090 1.0000 1.0000
0.500 0.3952 0.02150 0.01133 -0.1091 0.9990 1.0000
0.750 0.4327 0.02209 0.01166 -0.1117 0.9909 1.0000
1.000 0.4711 0.02268 0.01205 -0.1143 0.9831 1.0000
1.250 0.5071 0.02316 0.01241 -0.1165 0.9736 1.0000
1.500 0.5437 0.02362 0.01278 -0.1188 0.9640 1.0000
1.750 0.5811 0.02404 0.01315 -0.1211 0.9544 1.0000
2.000 0.6198 0.02440 0.01350 -0.1235 0.9446 1.0000
2.250 0.6552 0.02468 0.01385 -0.1253 0.9328 1.0000
2.500 0.6913 0.02489 0.01414 -0.1270 0.9204 1.0000
2.750 0.7280 0.02504 0.01439 -0.1287 0.9073 1.0000
3.000 0.7656 0.02509 0.01459 -0.1304 0.8936 1.0000
3.250 0.8045 0.02501 0.01479 -0.1321 0.8791 1.0000
3.500 0.8378 0.02493 0.01493 -0.1326 0.8611 1.0000
3.750 0.8758 0.02461 0.01486 -0.1336 0.8429 1.0000
4.000 0.9148 0.02410 0.01464 -0.1344 0.8232 1.0000
4.250 0.9532 0.02355 0.01441 -0.1349 0.7994 1.0000
4.500 0.9872 0.02311 0.01442 -0.1344 0.7681 1.0000
4.750 1.0225 0.02260 0.01421 -0.1340 0.7273 1.0000
5.000 1.0589 0.02214 0.01395 -0.1333 0.6678 1.0000
5.250 1.0934 0.02210 0.01381 -0.1323 0.5750 1.0000
5.500 1.1161 0.02301 0.01425 -0.1299 0.4626 1.0000
5.750 1.1298 0.02460 0.01530 -0.1270 0.3549 1.0000
6.000 1.1409 0.02664 0.01674 -0.1243 0.2489 1.0000
6.250 1.1516 0.02940 0.01858 -0.1223 0.1319 1.0000
6.500 1.1671 0.03245 0.02101 -0.1211 0.0553 1.0000
6.750 1.1851 0.03488 0.02355 -0.1194 0.0399 1.0000
7.000 1.2022 0.03743 0.02620 -0.1176 0.0345 1.0000
7.250 1.2242 0.03999 0.02917 -0.1159 0.0315 1.0000
7.500 1.2488 0.04297 0.03252 -0.1147 0.0292 1.0000
7.750 1.2731 0.04634 0.03629 -0.1137 0.0277 1.0000
8.000 1.2932 0.04994 0.04034 -0.1123 0.0264 1.0000
8.250 1.3072 0.05350 0.04429 -0.1106 0.0250 1.0000
8.500 1.3155 0.05760 0.04875 -0.1087 0.0236 1.0000
8.750 1.3188 0.06229 0.05387 -0.1063 0.0228 1.0000
9.000 1.3194 0.06623 0.05837 -0.1035 0.0223 1.0000
9.250 1.3145 0.07045 0.06309 -0.1005 0.0219 1.0000
9.500 1.3045 0.07467 0.06771 -0.0976 0.0217 1.0000
9.750 1.2895 0.07877 0.07213 -0.0945 0.0217 1.0000
10.000 1.2722 0.08318 0.07683 -0.0924 0.0217 1.0000
10.250 1.2538 0.08806 0.08196 -0.0913 0.0218 1.0000
10.500 1.2352 0.09343 0.08754 -0.0917 0.0220 1.0000
10.750 1.2163 0.09946 0.09376 -0.0934 0.0222 1.0000
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Polar data table (+)
Polar graphs
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