EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 50,000 Max Cl/Cd: 25.96 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e428-il-50000-n5.txt Download as CSV file: xf-e428-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 428 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7823 0.07500 0.06763 -0.0175 1.0000 0.0984
-10.750 -0.8038 0.06771 0.06033 -0.0226 1.0000 0.1010
-10.500 -0.8827 0.05301 0.04527 -0.0307 1.0000 0.0924
-10.250 -0.9026 0.04779 0.03957 -0.0316 1.0000 0.0965
-10.000 -0.8882 0.04804 0.03995 -0.0307 1.0000 0.1066
-9.750 -0.8708 0.04868 0.04066 -0.0297 1.0000 0.1176
-9.500 -0.8602 0.04747 0.03935 -0.0291 1.0000 0.1261
-9.250 -0.8542 0.04485 0.03639 -0.0288 1.0000 0.1332
-9.000 -0.8396 0.04309 0.03448 -0.0281 1.0000 0.1388
-8.750 -0.8247 0.04128 0.03244 -0.0275 1.0000 0.1453
-8.500 -0.8103 0.03911 0.02997 -0.0270 1.0000 0.1515
-8.250 -0.7906 0.03786 0.02860 -0.0263 1.0000 0.1575
-8.000 -0.7742 0.03580 0.02618 -0.0258 1.0000 0.1649
-7.750 -0.7524 0.03495 0.02530 -0.0250 1.0000 0.1717
-7.500 -0.7333 0.03324 0.02324 -0.0245 1.0000 0.1797
-7.250 -0.7109 0.03242 0.02239 -0.0238 1.0000 0.1869
-7.000 -0.6899 0.03116 0.02087 -0.0232 1.0000 0.1959
-6.750 -0.6672 0.03034 0.01997 -0.0225 1.0000 0.2044
-6.500 -0.6449 0.02939 0.01887 -0.0218 1.0000 0.2136
-6.250 -0.6224 0.02852 0.01780 -0.0212 1.0000 0.2244
-6.000 -0.5993 0.02789 0.01719 -0.0204 1.0000 0.2340
-5.750 -0.5764 0.02708 0.01622 -0.0198 1.0000 0.2453
-5.500 -0.5530 0.02634 0.01541 -0.0191 1.0000 0.2555
-5.250 -0.5295 0.02560 0.01463 -0.0184 1.0000 0.2652
-5.000 -0.5059 0.02482 0.01364 -0.0178 1.0000 0.2761
-4.750 -0.4822 0.02416 0.01308 -0.0170 1.0000 0.2847
-4.500 -0.4584 0.02349 0.01232 -0.0163 1.0000 0.2954
-4.250 -0.4349 0.02290 0.01172 -0.0155 1.0000 0.3059
-4.000 -0.4114 0.02232 0.01116 -0.0147 1.0000 0.3163
-3.750 -0.3879 0.02179 0.01059 -0.0140 1.0000 0.3283
-3.500 -0.3648 0.02130 0.01014 -0.0131 1.0000 0.3400
-3.250 -0.3417 0.02084 0.00976 -0.0123 1.0000 0.3528
-3.000 -0.3187 0.02041 0.00939 -0.0115 1.0000 0.3666
-2.750 -0.2966 0.02002 0.00906 -0.0106 1.0000 0.3814
-2.500 -0.2749 0.01967 0.00881 -0.0096 1.0000 0.3976
-2.250 -0.2539 0.01936 0.00861 -0.0086 1.0000 0.4148
-2.000 -0.2339 0.01908 0.00847 -0.0075 1.0000 0.4342
-1.750 -0.2148 0.01886 0.00840 -0.0063 1.0000 0.4562
-1.500 -0.1934 0.01868 0.00839 -0.0057 0.9976 0.4827
-1.250 -0.1500 0.01850 0.00847 -0.0090 0.9776 0.5237
-1.000 -0.1074 0.01832 0.00857 -0.0117 0.9579 0.5722
-0.750 -0.0646 0.01815 0.00867 -0.0141 0.9380 0.6275
-0.500 -0.0226 0.01794 0.00870 -0.0157 0.9118 0.6836
-0.250 0.0183 0.01770 0.00865 -0.0166 0.8805 0.7389
0.000 0.0562 0.01750 0.00856 -0.0166 0.8468 0.7908
0.250 0.0937 0.01736 0.00847 -0.0166 0.8147 0.8418
0.500 0.1358 0.01727 0.00836 -0.0177 0.7822 0.8915
0.750 0.1836 0.01722 0.00821 -0.0203 0.7456 0.9378
1.000 0.2327 0.01719 0.00802 -0.0235 0.7055 0.9829
1.250 0.2611 0.01728 0.00791 -0.0235 0.6692 1.0000
1.500 0.2806 0.01744 0.00787 -0.0217 0.6346 1.0000
1.750 0.3009 0.01764 0.00786 -0.0200 0.5987 1.0000
2.000 0.3219 0.01788 0.00787 -0.0184 0.5610 1.0000
2.250 0.3435 0.01816 0.00794 -0.0169 0.5215 1.0000
2.500 0.3654 0.01850 0.00805 -0.0156 0.4820 1.0000
2.750 0.3877 0.01891 0.00820 -0.0144 0.4447 1.0000
3.000 0.4106 0.01937 0.00844 -0.0133 0.4117 1.0000
3.250 0.4346 0.01987 0.00876 -0.0126 0.3831 1.0000
3.500 0.4590 0.02042 0.00911 -0.0119 0.3604 1.0000
3.750 0.4840 0.02098 0.00953 -0.0114 0.3413 1.0000
4.000 0.5091 0.02157 0.01001 -0.0109 0.3250 1.0000
4.250 0.5342 0.02218 0.01052 -0.0104 0.3110 1.0000
4.500 0.5598 0.02281 0.01114 -0.0099 0.2984 1.0000
4.750 0.5852 0.02349 0.01181 -0.0094 0.2876 1.0000
5.000 0.6104 0.02420 0.01240 -0.0089 0.2780 1.0000
5.250 0.6358 0.02494 0.01325 -0.0085 0.2680 1.0000
5.500 0.6612 0.02574 0.01396 -0.0080 0.2603 1.0000
5.750 0.6861 0.02658 0.01496 -0.0076 0.2512 1.0000
6.000 0.7113 0.02742 0.01571 -0.0071 0.2439 1.0000
6.250 0.7354 0.02840 0.01693 -0.0066 0.2356 1.0000
6.500 0.7602 0.02928 0.01777 -0.0061 0.2286 1.0000
6.750 0.7831 0.03038 0.01911 -0.0056 0.2204 1.0000
7.000 0.8070 0.03133 0.02009 -0.0050 0.2132 1.0000
7.250 0.8289 0.03250 0.02148 -0.0044 0.2053 1.0000
7.500 0.8515 0.03349 0.02254 -0.0038 0.1977 1.0000
7.750 0.8724 0.03473 0.02398 -0.0032 0.1903 1.0000
8.000 0.8932 0.03591 0.02534 -0.0025 0.1830 1.0000
8.250 0.9145 0.03708 0.02657 -0.0018 0.1768 1.0000
8.500 0.9313 0.03880 0.02865 -0.0011 0.1697 1.0000
8.750 0.9535 0.03977 0.02961 -0.0004 0.1644 1.0000
9.000 0.9662 0.04206 0.03231 0.0004 0.1583 1.0000
9.250 0.9809 0.04400 0.03451 0.0012 0.1531 1.0000
9.500 1.0029 0.04502 0.03548 0.0019 0.1489 1.0000
9.750 1.0034 0.04852 0.03953 0.0028 0.1438 1.0000
10.000 1.0087 0.05119 0.04248 0.0036 0.1393 1.0000
10.250 1.0245 0.05270 0.04405 0.0044 0.1357 1.0000
10.500 1.0224 0.05615 0.04777 0.0052 0.1329 1.0000
10.750 0.9896 0.06226 0.05426 0.0052 0.1310 1.0000
11.000 0.9344 0.07063 0.06281 0.0027 0.1306 1.0000
11.250 0.8310 0.09254 0.08467 -0.0135 0.1301 1.0000
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Polar data table (+)
Polar graphs
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