E474 (14.09%) (e474-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 100,000 Max Cl/Cd: 35.53 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e474-il-100000-n5.txt Download as CSV file: xf-e474-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8040 0.10356 0.09747 -0.0149 1.0000 0.1025
-14.250 -1.0438 0.05909 0.05266 -0.0423 1.0000 0.1065
-14.000 -1.0741 0.05246 0.04582 -0.0458 1.0000 0.1083
-13.750 -1.0972 0.04757 0.04070 -0.0473 1.0000 0.1105
-13.500 -1.1167 0.04371 0.03656 -0.0473 1.0000 0.1128
-13.250 -1.1133 0.04238 0.03527 -0.0463 1.0000 0.1156
-13.000 -1.1136 0.04090 0.03373 -0.0448 1.0000 0.1186
-12.750 -1.1177 0.03918 0.03185 -0.0428 1.0000 0.1219
-12.500 -1.1248 0.03733 0.02973 -0.0400 1.0000 0.1252
-12.250 -1.1197 0.03648 0.02888 -0.0375 1.0000 0.1281
-12.000 -1.1139 0.03579 0.02817 -0.0349 1.0000 0.1313
-11.750 -1.1089 0.03480 0.02704 -0.0323 1.0000 0.1351
-11.500 -1.1056 0.03347 0.02541 -0.0296 1.0000 0.1393
-11.250 -1.0910 0.03301 0.02501 -0.0278 1.0000 0.1425
-11.000 -1.0783 0.03241 0.02434 -0.0258 1.0000 0.1463
-10.750 -1.0679 0.03148 0.02321 -0.0236 1.0000 0.1507
-10.500 -1.0551 0.03069 0.02229 -0.0216 1.0000 0.1546
-10.250 -1.0387 0.03026 0.02187 -0.0199 1.0000 0.1582
-10.000 -1.0240 0.02962 0.02110 -0.0179 1.0000 0.1625
-9.750 -1.0118 0.02874 0.01992 -0.0157 1.0000 0.1673
-9.500 -0.9933 0.02832 0.01958 -0.0142 1.0000 0.1706
-9.250 -0.9760 0.02784 0.01906 -0.0125 1.0000 0.1745
-9.000 -0.9601 0.02720 0.01825 -0.0106 1.0000 0.1791
-8.750 -0.9434 0.02656 0.01745 -0.0088 1.0000 0.1834
-8.500 -0.9243 0.02613 0.01705 -0.0073 1.0000 0.1869
-8.250 -0.9060 0.02564 0.01648 -0.0057 1.0000 0.1912
-8.000 -0.8886 0.02504 0.01568 -0.0040 1.0000 0.1961
-7.750 -0.8693 0.02453 0.01515 -0.0025 1.0000 0.1997
-7.500 -0.8496 0.02411 0.01473 -0.0010 1.0000 0.2036
-7.250 -0.8304 0.02363 0.01416 0.0005 1.0000 0.2081
-7.000 -0.8115 0.02312 0.01345 0.0021 1.0000 0.2130
-6.750 -0.7910 0.02268 0.01308 0.0034 1.0000 0.2166
-6.500 -0.7707 0.02227 0.01266 0.0048 1.0000 0.2207
-6.250 -0.7505 0.02184 0.01213 0.0062 1.0000 0.2254
-6.000 -0.7302 0.02140 0.01160 0.0076 1.0000 0.2300
-5.750 -0.7094 0.02103 0.01128 0.0089 1.0000 0.2339
-5.500 -0.6887 0.02066 0.01090 0.0102 1.0000 0.2386
-5.250 -0.6679 0.02030 0.01043 0.0115 1.0000 0.2435
-5.000 -0.6469 0.01993 0.01009 0.0128 1.0000 0.2478
-4.750 -0.6260 0.01961 0.00981 0.0141 1.0000 0.2525
-4.500 -0.6050 0.01932 0.00949 0.0153 1.0000 0.2577
-4.250 -0.5839 0.01901 0.00915 0.0166 1.0000 0.2626
-4.000 -0.5630 0.01873 0.00894 0.0178 1.0000 0.2672
-3.750 -0.5372 0.01849 0.00872 0.0181 0.9982 0.2733
-3.500 -0.4885 0.01824 0.00850 0.0138 0.9867 0.2809
-3.250 -0.4428 0.01797 0.00829 0.0103 0.9748 0.2887
-3.000 -0.3995 0.01768 0.00803 0.0073 0.9623 0.2969
-2.750 -0.3579 0.01736 0.00780 0.0047 0.9487 0.3057
-2.500 -0.3182 0.01702 0.00752 0.0027 0.9335 0.3145
-2.250 -0.2828 0.01668 0.00726 0.0015 0.9144 0.3241
-2.000 -0.2493 0.01632 0.00700 0.0008 0.8902 0.3339
-1.750 -0.2164 0.01600 0.00673 0.0004 0.8586 0.3456
-1.500 -0.1762 0.01562 0.00640 -0.0014 0.8163 0.3588
-1.250 -0.1325 0.01530 0.00602 -0.0036 0.7571 0.3752
-1.000 -0.0991 0.01519 0.00574 -0.0039 0.6885 0.3929
-0.750 -0.0726 0.01521 0.00558 -0.0031 0.6259 0.4118
-0.500 -0.0480 0.01524 0.00549 -0.0021 0.5725 0.4330
-0.250 -0.0239 0.01527 0.00544 -0.0010 0.5278 0.4588
0.000 0.0000 0.01528 0.00543 0.0000 0.4901 0.4900
0.250 0.0239 0.01527 0.00544 0.0010 0.4587 0.5278
0.500 0.0480 0.01524 0.00549 0.0021 0.4329 0.5724
0.750 0.0726 0.01521 0.00558 0.0031 0.4117 0.6258
1.000 0.0991 0.01519 0.00574 0.0039 0.3928 0.6884
1.250 0.1325 0.01530 0.00602 0.0036 0.3752 0.7569
1.500 0.1762 0.01562 0.00641 0.0014 0.3589 0.8162
1.750 0.2164 0.01599 0.00672 -0.0004 0.3456 0.8586
2.000 0.2493 0.01632 0.00700 -0.0008 0.3340 0.8902
2.250 0.2827 0.01667 0.00726 -0.0015 0.3240 0.9144
2.500 0.3182 0.01701 0.00752 -0.0027 0.3145 0.9335
2.750 0.3579 0.01736 0.00780 -0.0047 0.3056 0.9488
3.000 0.3996 0.01768 0.00803 -0.0073 0.2970 0.9624
3.250 0.4428 0.01797 0.00829 -0.0103 0.2887 0.9749
3.500 0.4885 0.01824 0.00849 -0.0138 0.2809 0.9867
3.750 0.5371 0.01848 0.00871 -0.0180 0.2731 0.9982
4.000 0.5630 0.01872 0.00894 -0.0178 0.2671 1.0000
4.250 0.5838 0.01901 0.00915 -0.0166 0.2626 1.0000
4.500 0.6049 0.01931 0.00948 -0.0153 0.2577 1.0000
4.750 0.6259 0.01961 0.00981 -0.0141 0.2524 1.0000
5.000 0.6468 0.01993 0.01008 -0.0128 0.2477 1.0000
5.250 0.6678 0.02030 0.01043 -0.0115 0.2436 1.0000
5.500 0.6887 0.02066 0.01090 -0.0102 0.2386 1.0000
5.750 0.7094 0.02102 0.01128 -0.0089 0.2340 1.0000
6.000 0.7301 0.02140 0.01160 -0.0076 0.2300 1.0000
6.250 0.7505 0.02184 0.01213 -0.0062 0.2254 1.0000
6.500 0.7707 0.02227 0.01266 -0.0048 0.2208 1.0000
6.750 0.7909 0.02268 0.01307 -0.0034 0.2166 1.0000
7.000 0.8115 0.02311 0.01344 -0.0021 0.2130 1.0000
7.250 0.8303 0.02363 0.01416 -0.0005 0.2082 1.0000
7.500 0.8496 0.02411 0.01473 0.0010 0.2036 1.0000
7.750 0.8693 0.02453 0.01515 0.0025 0.1998 1.0000
8.000 0.8886 0.02504 0.01568 0.0040 0.1961 1.0000
8.250 0.9060 0.02564 0.01648 0.0057 0.1912 1.0000
8.500 0.9243 0.02613 0.01705 0.0073 0.1869 1.0000
8.750 0.9434 0.02655 0.01744 0.0088 0.1834 1.0000
9.000 0.9601 0.02720 0.01824 0.0106 0.1792 1.0000
9.250 0.9760 0.02784 0.01905 0.0125 0.1745 1.0000
9.500 0.9933 0.02832 0.01957 0.0142 0.1706 1.0000
9.750 1.0118 0.02873 0.01991 0.0157 0.1673 1.0000
10.000 1.0241 0.02963 0.02110 0.0179 0.1625 1.0000
10.250 1.0388 0.03027 0.02188 0.0199 0.1582 1.0000
10.500 1.0552 0.03069 0.02229 0.0216 0.1546 1.0000
10.750 1.0680 0.03148 0.02321 0.0236 0.1507 1.0000
11.000 1.0784 0.03241 0.02434 0.0258 0.1463 1.0000
11.250 1.0912 0.03301 0.02500 0.0278 0.1425 1.0000
11.500 1.1058 0.03346 0.02541 0.0296 0.1393 1.0000
11.750 1.1092 0.03479 0.02703 0.0323 0.1351 1.0000
12.000 1.1143 0.03579 0.02817 0.0349 0.1313 1.0000
12.250 1.1201 0.03648 0.02888 0.0375 0.1281 1.0000
12.500 1.1252 0.03734 0.02974 0.0399 0.1252 1.0000
12.750 1.1182 0.03917 0.03184 0.0427 0.1218 1.0000
13.000 1.1143 0.04089 0.03372 0.0447 0.1186 1.0000
13.250 1.1142 0.04236 0.03524 0.0462 0.1156 1.0000
13.500 1.1176 0.04370 0.03654 0.0472 0.1128 1.0000
13.750 1.0979 0.04757 0.04071 0.0472 0.1104 1.0000
14.000 1.0753 0.05240 0.04577 0.0457 0.1082 1.0000
14.250 1.0460 0.05891 0.05248 0.0423 0.1063 1.0000
14.750 0.8490 0.09849 0.09243 0.0182 0.1016 1.0000
15.000 0.9138 0.08983 0.08373 0.0240 0.1004 1.0000
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Polar data table (+)
Polar graphs
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