EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.09 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e428-il-1000000.txt Download as CSV file: xf-e428-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0739 0.08662 0.08323 -0.0089 1.0000 0.0093
-15.750 -1.0871 0.08097 0.07752 -0.0119 1.0000 0.0094
-15.500 -1.1015 0.07526 0.07173 -0.0149 1.0000 0.0094
-15.250 -1.1166 0.06948 0.06586 -0.0180 1.0000 0.0093
-15.000 -1.1316 0.06358 0.05987 -0.0213 1.0000 0.0093
-14.750 -1.1480 0.05744 0.05363 -0.0248 1.0000 0.0093
-14.500 -1.1629 0.05136 0.04744 -0.0284 1.0000 0.0093
-14.250 -1.1790 0.04498 0.04092 -0.0327 1.0000 0.0093
-14.000 -1.1861 0.03998 0.03580 -0.0362 1.0000 0.0093
-13.750 -1.1948 0.03521 0.03090 -0.0396 1.0000 0.0094
-13.500 -1.2015 0.03157 0.02714 -0.0416 1.0000 0.0094
-13.250 -1.2085 0.02897 0.02442 -0.0415 1.0000 0.0094
-13.000 -1.2138 0.02727 0.02263 -0.0392 1.0000 0.0095
-12.750 -1.2098 0.02593 0.02121 -0.0372 1.0000 0.0096
-12.500 -1.2005 0.02464 0.01983 -0.0357 1.0000 0.0097
-12.250 -1.1876 0.02351 0.01863 -0.0345 1.0000 0.0098
-12.000 -1.1728 0.02244 0.01748 -0.0334 1.0000 0.0100
-11.750 -1.1563 0.02145 0.01642 -0.0324 1.0000 0.0101
-11.500 -1.1382 0.02055 0.01544 -0.0314 1.0000 0.0102
-11.250 -1.1192 0.01969 0.01451 -0.0305 1.0000 0.0104
-11.000 -1.0991 0.01889 0.01364 -0.0297 1.0000 0.0106
-10.750 -1.0781 0.01815 0.01283 -0.0289 1.0000 0.0107
-10.500 -1.0563 0.01748 0.01211 -0.0282 1.0000 0.0109
-10.250 -1.0340 0.01685 0.01141 -0.0275 1.0000 0.0111
-10.000 -1.0139 0.01586 0.01033 -0.0266 1.0000 0.0115
-9.750 -0.9916 0.01515 0.00957 -0.0258 1.0000 0.0118
-9.500 -0.9684 0.01456 0.00892 -0.0251 1.0000 0.0121
-9.250 -0.9447 0.01403 0.00835 -0.0245 1.0000 0.0125
-9.000 -0.9206 0.01355 0.00782 -0.0238 1.0000 0.0129
-8.750 -0.8963 0.01311 0.00734 -0.0231 1.0000 0.0133
-8.500 -0.8719 0.01268 0.00687 -0.0225 1.0000 0.0137
-8.250 -0.8479 0.01219 0.00634 -0.0217 1.0000 0.0146
-8.000 -0.8235 0.01177 0.00590 -0.0210 1.0000 0.0157
-7.750 -0.7994 0.01131 0.00544 -0.0202 1.0000 0.0186
-7.500 -0.7782 0.01042 0.00476 -0.0192 1.0000 0.0466
-7.250 -0.7537 0.01005 0.00444 -0.0185 1.0000 0.0566
-7.000 -0.7293 0.00969 0.00412 -0.0178 1.0000 0.0652
-6.750 -0.7051 0.00930 0.00382 -0.0170 1.0000 0.0772
-6.500 -0.6809 0.00895 0.00357 -0.0162 1.0000 0.0924
-6.250 -0.6562 0.00869 0.00337 -0.0155 1.0000 0.1036
-6.000 -0.6314 0.00847 0.00318 -0.0147 1.0000 0.1127
-5.750 -0.6068 0.00827 0.00301 -0.0140 1.0000 0.1206
-5.500 -0.5823 0.00807 0.00285 -0.0131 1.0000 0.1287
-5.250 -0.5497 0.00789 0.00271 -0.0140 0.9984 0.1377
-5.000 -0.5118 0.00770 0.00258 -0.0161 0.9947 0.1501
-4.750 -0.4755 0.00751 0.00245 -0.0177 0.9897 0.1615
-4.500 -0.4356 0.00734 0.00233 -0.0201 0.9834 0.1714
-4.250 -0.3970 0.00720 0.00221 -0.0221 0.9714 0.1805
-4.000 -0.3578 0.00705 0.00210 -0.0243 0.9495 0.1918
-3.750 -0.3243 0.00698 0.00196 -0.0250 0.9049 0.2000
-3.500 -0.2985 0.00703 0.00187 -0.0242 0.8567 0.2074
-3.250 -0.2727 0.00707 0.00177 -0.0234 0.8168 0.2139
-3.000 -0.2463 0.00709 0.00169 -0.0227 0.7820 0.2207
-2.500 -0.1919 0.00710 0.00155 -0.0219 0.7271 0.2340
-2.250 -0.1645 0.00711 0.00149 -0.0215 0.7020 0.2412
-2.000 -0.1369 0.00709 0.00142 -0.0212 0.6795 0.2502
-1.750 -0.1092 0.00709 0.00137 -0.0209 0.6569 0.2574
-1.500 -0.0816 0.00709 0.00131 -0.0206 0.6329 0.2653
-1.250 -0.0538 0.00709 0.00127 -0.0203 0.6104 0.2738
-1.000 -0.0261 0.00708 0.00123 -0.0201 0.5883 0.2837
-0.750 0.0017 0.00709 0.00119 -0.0198 0.5646 0.2948
-0.500 0.0293 0.00709 0.00116 -0.0195 0.5383 0.3093
0.000 0.0841 0.00705 0.00113 -0.0190 0.4847 0.3575
0.250 0.1111 0.00701 0.00113 -0.0187 0.4572 0.3970
0.500 0.1380 0.00698 0.00114 -0.0184 0.4268 0.4424
0.750 0.1648 0.00699 0.00118 -0.0180 0.3903 0.4876
1.000 0.1913 0.00709 0.00123 -0.0177 0.3438 0.5276
1.250 0.2178 0.00723 0.00130 -0.0173 0.2991 0.5625
1.500 0.2446 0.00732 0.00139 -0.0169 0.2706 0.5977
1.750 0.2717 0.00739 0.00147 -0.0166 0.2519 0.6305
2.000 0.2989 0.00744 0.00156 -0.0162 0.2381 0.6600
2.250 0.3261 0.00750 0.00165 -0.0159 0.2258 0.6886
2.500 0.3532 0.00755 0.00174 -0.0155 0.2155 0.7172
2.750 0.3802 0.00757 0.00184 -0.0150 0.2066 0.7485
3.000 0.4067 0.00761 0.00194 -0.0145 0.1978 0.7828
3.250 0.4330 0.00761 0.00205 -0.0139 0.1917 0.8202
3.500 0.4586 0.00761 0.00215 -0.0131 0.1852 0.8608
3.750 0.4836 0.00760 0.00227 -0.0121 0.1777 0.9135
4.000 0.5268 0.00765 0.00238 -0.0151 0.1714 0.9695
4.250 0.5678 0.00785 0.00252 -0.0178 0.1641 1.0000
4.500 0.5946 0.00796 0.00263 -0.0173 0.1607 1.0000
4.750 0.6213 0.00810 0.00274 -0.0169 0.1560 1.0000
5.000 0.6478 0.00828 0.00289 -0.0165 0.1511 1.0000
5.250 0.6746 0.00843 0.00303 -0.0161 0.1471 1.0000
5.500 0.7017 0.00856 0.00316 -0.0157 0.1430 1.0000
5.750 0.7284 0.00874 0.00330 -0.0153 0.1380 1.0000
6.000 0.7551 0.00893 0.00348 -0.0149 0.1336 1.0000
6.250 0.7822 0.00906 0.00362 -0.0146 0.1300 1.0000
6.500 0.8090 0.00925 0.00378 -0.0142 0.1250 1.0000
6.750 0.8356 0.00946 0.00397 -0.0138 0.1200 1.0000
7.000 0.8625 0.00962 0.00413 -0.0135 0.1157 1.0000
7.250 0.8888 0.00986 0.00433 -0.0130 0.1091 1.0000
7.500 0.9155 0.01006 0.00453 -0.0127 0.1036 1.0000
7.750 0.9415 0.01034 0.00476 -0.0123 0.0957 1.0000
8.000 0.9674 0.01062 0.00501 -0.0118 0.0877 1.0000
8.250 0.9931 0.01094 0.00529 -0.0114 0.0795 1.0000
8.500 1.0184 0.01130 0.00561 -0.0109 0.0720 1.0000
8.750 1.0434 0.01169 0.00596 -0.0103 0.0655 1.0000
9.000 1.0686 0.01204 0.00630 -0.0099 0.0610 1.0000
9.250 1.0935 0.01243 0.00668 -0.0093 0.0568 1.0000
9.500 1.1187 0.01277 0.00702 -0.0088 0.0537 1.0000
9.750 1.1430 0.01321 0.00745 -0.0082 0.0499 1.0000
10.000 1.1680 0.01353 0.00779 -0.0077 0.0468 1.0000
10.250 1.1918 0.01400 0.00825 -0.0071 0.0422 1.0000
10.500 1.2155 0.01448 0.00870 -0.0065 0.0353 1.0000
10.750 1.2361 0.01530 0.00941 -0.0055 0.0234 1.0000
11.000 1.2577 0.01598 0.01009 -0.0047 0.0208 1.0000
11.250 1.2793 0.01664 0.01078 -0.0038 0.0193 1.0000
11.500 1.3011 0.01722 0.01142 -0.0030 0.0185 1.0000
11.750 1.3219 0.01789 0.01215 -0.0020 0.0178 1.0000
12.000 1.3411 0.01868 0.01299 -0.0010 0.0171 1.0000
12.250 1.3583 0.01963 0.01401 0.0003 0.0165 1.0000
12.500 1.3776 0.02030 0.01475 0.0014 0.0162 1.0000
12.750 1.3957 0.02102 0.01555 0.0026 0.0158 1.0000
13.000 1.4124 0.02180 0.01640 0.0039 0.0154 1.0000
13.250 1.4271 0.02268 0.01734 0.0054 0.0150 1.0000
13.500 1.4396 0.02362 0.01836 0.0071 0.0147 1.0000
13.750 1.4466 0.02468 0.01950 0.0095 0.0144 1.0000
14.000 1.4461 0.02594 0.02084 0.0127 0.0142 1.0000
14.250 1.4428 0.02751 0.02251 0.0155 0.0140 1.0000
14.500 1.4365 0.02956 0.02468 0.0174 0.0138 1.0000
14.750 1.4272 0.03233 0.02758 0.0183 0.0137 1.0000
15.000 1.4194 0.03554 0.03092 0.0179 0.0136 1.0000
15.250 1.4168 0.03864 0.03412 0.0170 0.0135 1.0000
15.500 1.4093 0.04270 0.03831 0.0152 0.0134 1.0000
15.750 1.3969 0.04780 0.04355 0.0125 0.0134 1.0000
16.000 1.3808 0.05380 0.04969 0.0092 0.0133 1.0000
16.250 1.3566 0.06134 0.05739 0.0049 0.0133 1.0000
16.500 1.3294 0.06960 0.06581 0.0002 0.0133 1.0000
16.750 1.2954 0.07912 0.07549 -0.0051 0.0134 1.0000
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Polar data table (+)
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