EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.12 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e328-il-1000000-n5.txt Download as CSV file: xf-e328-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 328 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2677 0.09212 0.08978 -0.0370 0.7521 0.0048
-10.500 -0.2673 0.08820 0.08579 -0.0384 0.7330 0.0048
-10.250 -0.3713 0.09285 0.09115 -0.0348 0.9415 0.0049
-10.000 -0.3283 0.08426 0.08208 -0.0516 0.8310 0.0046
-9.750 -0.3346 0.08053 0.07814 -0.0526 0.7773 0.0045
-9.500 -0.3494 0.07436 0.07191 -0.0563 0.7528 0.0043
-9.250 -0.3635 0.06931 0.06676 -0.0601 0.7268 0.0043
-8.250 -0.5907 0.02264 0.01794 -0.0357 0.7032 0.0031
-8.000 -0.5768 0.02041 0.01531 -0.0336 0.6863 0.0032
-7.750 -0.5583 0.01898 0.01359 -0.0321 0.6703 0.0032
-7.500 -0.5368 0.01806 0.01245 -0.0310 0.6557 0.0033
-7.250 -0.5163 0.01687 0.01102 -0.0298 0.6412 0.0032
-7.000 -0.4955 0.01555 0.00942 -0.0286 0.6279 0.0035
-6.750 -0.4725 0.01486 0.00859 -0.0278 0.6150 0.0036
-6.500 -0.4490 0.01428 0.00789 -0.0270 0.6031 0.0037
-6.250 -0.4249 0.01384 0.00735 -0.0263 0.5919 0.0038
-6.000 -0.3999 0.01360 0.00705 -0.0258 0.5805 0.0040
-5.750 -0.3757 0.01316 0.00651 -0.0251 0.5693 0.0041
-5.500 -0.3511 0.01283 0.00610 -0.0244 0.5581 0.0043
-5.250 -0.3268 0.01246 0.00564 -0.0238 0.5479 0.0044
-5.000 -0.3021 0.01213 0.00523 -0.0231 0.5389 0.0045
-4.750 -0.2777 0.01182 0.00484 -0.0225 0.5297 0.0047
-4.500 -0.2525 0.01157 0.00454 -0.0219 0.5200 0.0049
-4.250 -0.2278 0.01132 0.00422 -0.0213 0.5107 0.0050
-4.000 -0.2027 0.01109 0.00393 -0.0207 0.5020 0.0051
-3.750 -0.1775 0.01086 0.00365 -0.0201 0.4947 0.0051
-3.500 -0.1527 0.01060 0.00334 -0.0195 0.4865 0.0054
-3.250 -0.1275 0.01040 0.00310 -0.0190 0.4790 0.0057
-3.000 -0.1017 0.01027 0.00292 -0.0186 0.4707 0.0061
-2.750 -0.0760 0.01011 0.00273 -0.0181 0.4638 0.0067
-2.500 -0.0499 0.00999 0.00258 -0.0177 0.4569 0.0072
-2.250 -0.0242 0.00984 0.00239 -0.0173 0.4503 0.0084
-2.000 0.0019 0.00972 0.00224 -0.0169 0.4435 0.0102
-1.750 0.0276 0.00959 0.00212 -0.0164 0.4366 0.0176
-1.500 0.0538 0.00946 0.00202 -0.0161 0.4312 0.0289
-1.250 0.0799 0.00936 0.00194 -0.0158 0.4252 0.0418
-1.000 0.1050 0.00918 0.00186 -0.0153 0.4194 0.0816
-0.750 0.1273 0.00872 0.00176 -0.0144 0.4143 0.1977
-0.500 0.1243 0.00649 0.00149 -0.0091 0.4100 0.7663
-0.250 0.1510 0.00655 0.00155 -0.0088 0.4047 0.7974
0.000 0.1787 0.00661 0.00159 -0.0086 0.4000 0.8116
0.250 0.2059 0.00671 0.00166 -0.0083 0.3944 0.8259
0.500 0.2332 0.00682 0.00173 -0.0081 0.3892 0.8336
0.750 0.2610 0.00690 0.00178 -0.0080 0.3851 0.8407
1.000 0.2888 0.00696 0.00182 -0.0080 0.3804 0.8444
1.250 0.3168 0.00703 0.00183 -0.0080 0.3752 0.8455
1.500 0.3452 0.00708 0.00185 -0.0082 0.3711 0.8465
1.750 0.3735 0.00714 0.00187 -0.0083 0.3669 0.8474
2.000 0.4016 0.00721 0.00189 -0.0084 0.3621 0.8484
2.250 0.4296 0.00728 0.00193 -0.0085 0.3577 0.8496
2.500 0.4579 0.00734 0.00197 -0.0087 0.3541 0.8507
2.750 0.4860 0.00741 0.00201 -0.0088 0.3496 0.8517
3.000 0.5138 0.00749 0.00206 -0.0089 0.3453 0.8527
3.250 0.5419 0.00757 0.00211 -0.0090 0.3416 0.8536
3.500 0.5700 0.00764 0.00216 -0.0092 0.3376 0.8544
3.750 0.5978 0.00773 0.00223 -0.0093 0.3331 0.8553
4.000 0.6252 0.00783 0.00231 -0.0093 0.3285 0.8562
4.250 0.6531 0.00789 0.00238 -0.0095 0.3249 0.8573
4.500 0.6807 0.00797 0.00246 -0.0095 0.3204 0.8584
4.750 0.7079 0.00808 0.00256 -0.0095 0.3158 0.8596
5.000 0.7352 0.00817 0.00266 -0.0096 0.3117 0.8608
5.250 0.7627 0.00826 0.00275 -0.0097 0.3072 0.8619
5.500 0.7897 0.00839 0.00287 -0.0097 0.3015 0.8630
5.750 0.8167 0.00851 0.00298 -0.0097 0.2965 0.8641
6.000 0.8438 0.00862 0.00310 -0.0097 0.2908 0.8653
6.250 0.8702 0.00878 0.00324 -0.0097 0.2848 0.8666
6.500 0.8972 0.00890 0.00337 -0.0097 0.2793 0.8678
6.750 0.9235 0.00906 0.00352 -0.0096 0.2724 0.8690
7.000 0.9498 0.00921 0.00367 -0.0096 0.2660 0.8702
7.250 0.9757 0.00940 0.00384 -0.0095 0.2577 0.8713
7.500 1.0013 0.00957 0.00402 -0.0093 0.2500 0.8727
7.750 1.0260 0.00980 0.00423 -0.0090 0.2408 0.8743
8.000 1.0510 0.01000 0.00444 -0.0087 0.2321 0.8760
8.250 1.0754 0.01023 0.00467 -0.0084 0.2232 0.8777
8.500 1.0990 0.01053 0.00493 -0.0079 0.2119 0.8794
8.750 1.1222 0.01083 0.00521 -0.0074 0.2007 0.8812
9.000 1.1452 0.01114 0.00550 -0.0069 0.1892 0.8830
9.250 1.1670 0.01152 0.00584 -0.0062 0.1760 0.8849
9.500 1.1880 0.01193 0.00621 -0.0054 0.1628 0.8868
9.750 1.2077 0.01237 0.00660 -0.0044 0.1492 0.8889
10.000 1.2269 0.01280 0.00702 -0.0033 0.1371 0.8913
10.250 1.2435 0.01335 0.00751 -0.0018 0.1222 0.8941
10.500 1.2604 0.01385 0.00799 -0.0004 0.1107 0.8972
10.750 1.2765 0.01436 0.00848 0.0012 0.1004 0.9004
11.000 1.2909 0.01484 0.00895 0.0031 0.0924 0.9039
11.250 1.2997 0.01538 0.00949 0.0059 0.0831 0.9090
11.500 1.3062 0.01606 0.01015 0.0091 0.0727 0.9153
11.750 1.3166 0.01659 0.01072 0.0115 0.0675 0.9214
12.000 1.3203 0.01737 0.01151 0.0147 0.0584 0.9308
12.250 1.3261 0.01809 0.01227 0.0175 0.0540 0.9430
12.500 1.3363 0.01889 0.01314 0.0190 0.0490 0.9626
13.000 1.3547 0.02153 0.01581 0.0202 0.0366 1.0000
13.500 1.3606 0.02466 0.01899 0.0227 0.0293 1.0000
13.750 1.3586 0.02685 0.02120 0.0236 0.0247 1.0000
14.000 1.3630 0.02867 0.02308 0.0241 0.0237 1.0000
14.250 1.3610 0.03117 0.02562 0.0244 0.0206 1.0000
14.500 1.3665 0.03307 0.02762 0.0245 0.0211 1.0000
14.750 1.3615 0.03606 0.03065 0.0244 0.0182 1.0000
15.000 1.3581 0.03898 0.03363 0.0242 0.0166 1.0000
15.250 1.3517 0.04228 0.03698 0.0239 0.0148 1.0000
15.500 1.3492 0.04527 0.04006 0.0235 0.0142 1.0000
15.750 1.3431 0.04866 0.04352 0.0229 0.0131 1.0000
16.000 1.3373 0.05215 0.04709 0.0222 0.0125 1.0000
16.250 1.3321 0.05568 0.05069 0.0214 0.0121 1.0000
16.500 1.3267 0.05928 0.05438 0.0204 0.0115 1.0000
16.750 1.3196 0.06324 0.05841 0.0193 0.0105 1.0000
17.000 1.3133 0.06717 0.06241 0.0181 0.0101 1.0000
17.250 1.3050 0.07141 0.06672 0.0167 0.0091 1.0000
17.500 1.2992 0.07544 0.07083 0.0153 0.0086 1.0000
17.750 1.2941 0.07946 0.07494 0.0138 0.0084 1.0000
18.000 1.2883 0.08361 0.07915 0.0122 0.0080 1.0000
18.250 1.2794 0.08829 0.08390 0.0104 0.0072 1.0000
18.500 1.2746 0.09247 0.08817 0.0086 0.0073 1.0000
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