EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.14 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e428-il-1000000-n5.txt Download as CSV file: xf-e428-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0995 0.08118 0.07767 -0.0108 1.0000 0.0066
-15.500 -1.1335 0.07231 0.06868 -0.0157 1.0000 0.0066
-15.250 -1.1746 0.06230 0.05853 -0.0215 1.0000 0.0065
-15.000 -1.2079 0.05309 0.04916 -0.0271 1.0000 0.0065
-14.750 -1.2338 0.04463 0.04051 -0.0331 1.0000 0.0065
-14.500 -1.2519 0.03779 0.03349 -0.0383 1.0000 0.0065
-14.250 -1.2612 0.03330 0.02886 -0.0413 1.0000 0.0065
-14.000 -1.2688 0.03014 0.02557 -0.0423 1.0000 0.0065
-13.750 -1.2727 0.02818 0.02350 -0.0412 1.0000 0.0065
-13.500 -1.2738 0.02681 0.02204 -0.0388 1.0000 0.0066
-13.250 -1.2658 0.02561 0.02076 -0.0372 1.0000 0.0066
-13.000 -1.2530 0.02460 0.01967 -0.0360 1.0000 0.0067
-12.750 -1.2411 0.02339 0.01836 -0.0347 1.0000 0.0067
-12.500 -1.2285 0.02211 0.01698 -0.0334 1.0000 0.0069
-12.250 -1.2113 0.02117 0.01598 -0.0325 1.0000 0.0069
-12.000 -1.1933 0.02026 0.01500 -0.0316 1.0000 0.0071
-11.750 -1.1735 0.01949 0.01416 -0.0307 1.0000 0.0072
-11.500 -1.1526 0.01880 0.01342 -0.0300 1.0000 0.0074
-11.250 -1.1310 0.01816 0.01273 -0.0293 1.0000 0.0075
-11.000 -1.1088 0.01755 0.01206 -0.0286 1.0000 0.0077
-10.750 -1.0862 0.01697 0.01144 -0.0280 1.0000 0.0079
-10.500 -1.0633 0.01642 0.01084 -0.0273 1.0000 0.0080
-10.250 -1.0400 0.01589 0.01027 -0.0267 1.0000 0.0082
-10.000 -1.0164 0.01539 0.00972 -0.0261 1.0000 0.0084
-9.750 -0.9924 0.01492 0.00921 -0.0255 1.0000 0.0085
-9.500 -0.9683 0.01448 0.00872 -0.0249 1.0000 0.0086
-9.250 -0.9442 0.01401 0.00822 -0.0243 1.0000 0.0089
-9.000 -0.9202 0.01351 0.00768 -0.0236 1.0000 0.0092
-8.750 -0.8959 0.01309 0.00722 -0.0230 1.0000 0.0095
-8.500 -0.8713 0.01270 0.00681 -0.0224 1.0000 0.0098
-8.250 -0.8466 0.01234 0.00643 -0.0217 1.0000 0.0102
-8.000 -0.8218 0.01201 0.00607 -0.0211 1.0000 0.0106
-7.750 -0.7970 0.01170 0.00574 -0.0204 1.0000 0.0111
-7.500 -0.7724 0.01136 0.00539 -0.0197 1.0000 0.0120
-7.250 -0.7477 0.01103 0.00505 -0.0190 1.0000 0.0133
-7.000 -0.7256 0.01026 0.00442 -0.0180 1.0000 0.0347
-6.750 -0.6980 0.00985 0.00410 -0.0180 0.9987 0.0474
-6.500 -0.6648 0.00955 0.00383 -0.0191 0.9935 0.0539
-6.250 -0.6322 0.00928 0.00358 -0.0200 0.9875 0.0597
-6.000 -0.5975 0.00898 0.00333 -0.0214 0.9807 0.0676
-5.750 -0.5624 0.00863 0.00307 -0.0230 0.9697 0.0825
-5.500 -0.5258 0.00836 0.00285 -0.0247 0.9494 0.0964
-5.250 -0.4925 0.00817 0.00265 -0.0257 0.9111 0.1080
-5.000 -0.4664 0.00808 0.00247 -0.0250 0.8686 0.1171
-4.750 -0.4407 0.00806 0.00233 -0.0242 0.8298 0.1233
-4.500 -0.4149 0.00802 0.00219 -0.0235 0.7916 0.1311
-4.250 -0.3885 0.00796 0.00206 -0.0230 0.7595 0.1414
-4.000 -0.3618 0.00790 0.00194 -0.0226 0.7300 0.1533
-3.750 -0.3348 0.00786 0.00183 -0.0222 0.7011 0.1624
-3.500 -0.3075 0.00781 0.00174 -0.0219 0.6740 0.1714
-3.250 -0.2801 0.00782 0.00165 -0.0215 0.6454 0.1780
-3.000 -0.2527 0.00781 0.00157 -0.0212 0.6150 0.1847
-2.750 -0.2250 0.00781 0.00149 -0.0210 0.5880 0.1911
-2.500 -0.1972 0.00781 0.00143 -0.0207 0.5648 0.1972
-2.250 -0.1694 0.00780 0.00137 -0.0205 0.5410 0.2053
-2.000 -0.1416 0.00780 0.00132 -0.0203 0.5180 0.2132
-1.750 -0.1137 0.00781 0.00128 -0.0200 0.4950 0.2201
-1.500 -0.0858 0.00785 0.00124 -0.0198 0.4691 0.2251
-1.250 -0.0580 0.00789 0.00121 -0.0196 0.4440 0.2310
-1.000 -0.0300 0.00792 0.00119 -0.0194 0.4216 0.2373
-0.750 -0.0021 0.00799 0.00117 -0.0192 0.3951 0.2425
-0.500 0.0254 0.00808 0.00117 -0.0189 0.3596 0.2496
-0.250 0.0528 0.00821 0.00118 -0.0187 0.3182 0.2572
0.000 0.0802 0.00831 0.00120 -0.0185 0.2859 0.2667
0.250 0.1079 0.00839 0.00122 -0.0183 0.2634 0.2782
0.500 0.1357 0.00843 0.00125 -0.0180 0.2476 0.2917
0.750 0.1635 0.00844 0.00128 -0.0178 0.2345 0.3092
1.000 0.1912 0.00845 0.00131 -0.0176 0.2234 0.3297
1.250 0.2189 0.00844 0.00135 -0.0174 0.2139 0.3535
1.500 0.2467 0.00840 0.00139 -0.0172 0.2068 0.3852
1.750 0.2743 0.00837 0.00144 -0.0170 0.1993 0.4190
2.000 0.3020 0.00836 0.00150 -0.0168 0.1927 0.4502
2.250 0.3297 0.00836 0.00157 -0.0166 0.1858 0.4802
2.500 0.3573 0.00839 0.00164 -0.0163 0.1782 0.5091
2.750 0.3849 0.00839 0.00172 -0.0161 0.1722 0.5406
3.000 0.4123 0.00842 0.00181 -0.0158 0.1659 0.5715
3.250 0.4400 0.00844 0.00191 -0.0156 0.1617 0.5998
3.500 0.4675 0.00847 0.00201 -0.0153 0.1572 0.6258
3.750 0.4947 0.00854 0.00212 -0.0150 0.1499 0.6548
4.000 0.5221 0.00857 0.00224 -0.0146 0.1460 0.6832
4.250 0.5494 0.00862 0.00236 -0.0143 0.1424 0.7089
4.500 0.5764 0.00868 0.00248 -0.0139 0.1382 0.7384
4.750 0.6030 0.00873 0.00262 -0.0135 0.1334 0.7711
5.000 0.6293 0.00874 0.00276 -0.0129 0.1302 0.8082
5.250 0.6534 0.00870 0.00291 -0.0118 0.1260 0.8715
5.500 0.6962 0.00870 0.00308 -0.0147 0.1195 0.9787
5.750 0.7273 0.00887 0.00323 -0.0153 0.1143 1.0000
6.000 0.7539 0.00907 0.00340 -0.0149 0.1089 1.0000
6.250 0.7807 0.00925 0.00356 -0.0145 0.1041 1.0000
6.500 0.8070 0.00949 0.00375 -0.0141 0.0968 1.0000
6.750 0.8336 0.00970 0.00395 -0.0137 0.0904 1.0000
7.000 0.8597 0.00998 0.00418 -0.0133 0.0825 1.0000
7.250 0.8854 0.01030 0.00444 -0.0128 0.0731 1.0000
7.500 0.9109 0.01066 0.00474 -0.0123 0.0638 1.0000
8.000 0.9623 0.01130 0.00533 -0.0114 0.0540 1.0000
8.250 0.9879 0.01162 0.00564 -0.0109 0.0508 1.0000
8.500 1.0137 0.01191 0.00594 -0.0105 0.0485 1.0000
8.750 1.0394 0.01220 0.00624 -0.0100 0.0463 1.0000
9.000 1.0645 0.01257 0.00660 -0.0095 0.0434 1.0000
9.250 1.0898 0.01288 0.00692 -0.0091 0.0406 1.0000
9.500 1.1144 0.01329 0.00731 -0.0085 0.0362 1.0000
9.750 1.1374 0.01389 0.00783 -0.0078 0.0242 1.0000
10.000 1.1598 0.01455 0.00845 -0.0070 0.0185 1.0000
10.250 1.1832 0.01506 0.00898 -0.0064 0.0169 1.0000
10.500 1.2068 0.01552 0.00947 -0.0057 0.0160 1.0000
10.750 1.2302 0.01599 0.00998 -0.0050 0.0154 1.0000
11.000 1.2530 0.01651 0.01053 -0.0043 0.0147 1.0000
11.250 1.2749 0.01709 0.01115 -0.0035 0.0141 1.0000
11.500 1.2965 0.01769 0.01179 -0.0027 0.0136 1.0000
11.750 1.3185 0.01820 0.01235 -0.0019 0.0133 1.0000
12.000 1.3399 0.01875 0.01296 -0.0010 0.0130 1.0000
12.250 1.3606 0.01933 0.01359 -0.0001 0.0127 1.0000
12.500 1.3805 0.01995 0.01427 0.0009 0.0124 1.0000
12.750 1.3994 0.02062 0.01499 0.0019 0.0121 1.0000
13.000 1.4171 0.02135 0.01578 0.0031 0.0118 1.0000
13.250 1.4330 0.02217 0.01665 0.0045 0.0115 1.0000
13.500 1.4468 0.02307 0.01761 0.0060 0.0112 1.0000
13.750 1.4591 0.02398 0.01859 0.0078 0.0110 1.0000
14.000 1.4684 0.02478 0.01947 0.0100 0.0109 1.0000
14.250 1.4752 0.02566 0.02042 0.0125 0.0107 1.0000
14.500 1.4801 0.02673 0.02157 0.0147 0.0106 1.0000
14.750 1.4836 0.02800 0.02293 0.0166 0.0105 1.0000
15.000 1.4849 0.02961 0.02463 0.0181 0.0104 1.0000
15.250 1.4850 0.03157 0.02668 0.0189 0.0102 1.0000
15.500 1.4838 0.03393 0.02914 0.0191 0.0101 1.0000
15.750 1.4798 0.03691 0.03224 0.0186 0.0100 1.0000
16.000 1.4749 0.04035 0.03579 0.0174 0.0099 1.0000
16.250 1.4646 0.04481 0.04039 0.0153 0.0099 1.0000
16.500 1.4514 0.05006 0.04578 0.0126 0.0098 1.0000
16.750 1.4265 0.05745 0.05334 0.0083 0.0098 1.0000
17.000 1.3901 0.06707 0.06317 0.0027 0.0099 1.0000
17.250 1.3436 0.07883 0.07515 -0.0040 0.0099 1.0000
17.500 1.2801 0.09379 0.09033 -0.0126 0.0101 1.0000
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Polar data table (+)
Polar graphs
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