EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 500,000 Max Cl/Cd: 74.49 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e428-il-500000.txt Download as CSV file: xf-e428-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9185 0.15672 0.15389 0.0294 1.0000 0.0144
-18.000 -0.9732 0.13784 0.13466 0.0177 1.0000 0.0140
-17.750 -0.9934 0.12835 0.12499 0.0117 1.0000 0.0138
-17.500 -1.0068 0.12076 0.11725 0.0070 1.0000 0.0137
-17.250 -1.0169 0.11427 0.11064 0.0030 1.0000 0.0137
-17.000 -1.0277 0.10797 0.10423 -0.0006 1.0000 0.0137
-16.750 -1.0355 0.10225 0.09842 -0.0040 1.0000 0.0137
-16.500 -1.0425 0.09680 0.09286 -0.0073 1.0000 0.0136
-16.250 -1.0500 0.09152 0.08748 -0.0102 1.0000 0.0136
-16.000 -1.0567 0.08650 0.08237 -0.0130 1.0000 0.0136
-15.750 -1.0637 0.08175 0.07754 -0.0154 1.0000 0.0137
-15.500 -1.0701 0.07724 0.07293 -0.0176 1.0000 0.0137
-15.250 -1.0763 0.07272 0.06832 -0.0201 1.0000 0.0137
-15.000 -1.0824 0.06837 0.06389 -0.0222 1.0000 0.0137
-14.750 -1.0885 0.06407 0.05951 -0.0243 1.0000 0.0137
-14.500 -1.0941 0.05979 0.05515 -0.0265 1.0000 0.0138
-14.250 -1.1015 0.05548 0.05077 -0.0285 1.0000 0.0138
-14.000 -1.1055 0.05131 0.04650 -0.0309 1.0000 0.0138
-13.750 -1.1125 0.04698 0.04209 -0.0332 1.0000 0.0139
-13.500 -1.1180 0.04283 0.03784 -0.0356 1.0000 0.0140
-13.250 -1.1228 0.03893 0.03384 -0.0378 1.0000 0.0140
-13.000 -1.1287 0.03529 0.03010 -0.0396 1.0000 0.0142
-12.750 -1.1317 0.03253 0.02724 -0.0403 1.0000 0.0142
-12.500 -1.1379 0.03022 0.02483 -0.0394 1.0000 0.0143
-12.250 -1.1388 0.02868 0.02321 -0.0372 1.0000 0.0144
-12.000 -1.1333 0.02716 0.02161 -0.0357 1.0000 0.0146
-11.750 -1.1230 0.02584 0.02020 -0.0344 1.0000 0.0148
-11.500 -1.1099 0.02463 0.01891 -0.0332 1.0000 0.0151
-11.250 -1.0949 0.02349 0.01769 -0.0322 1.0000 0.0154
-11.000 -1.0782 0.02243 0.01655 -0.0312 1.0000 0.0158
-10.750 -1.0601 0.02147 0.01548 -0.0302 1.0000 0.0160
-10.500 -1.0407 0.02057 0.01449 -0.0293 1.0000 0.0163
-10.250 -1.0232 0.01938 0.01322 -0.0284 1.0000 0.0167
-10.000 -1.0034 0.01840 0.01218 -0.0275 1.0000 0.0172
-9.750 -0.9820 0.01759 0.01130 -0.0268 1.0000 0.0178
-9.500 -0.9596 0.01687 0.01050 -0.0260 1.0000 0.0185
-9.250 -0.9365 0.01624 0.00979 -0.0253 1.0000 0.0193
-9.000 -0.9140 0.01549 0.00900 -0.0246 1.0000 0.0208
-8.500 -0.8690 0.01394 0.00751 -0.0231 1.0000 0.0351
-8.250 -0.8461 0.01324 0.00694 -0.0224 1.0000 0.0558
-8.000 -0.8221 0.01274 0.00647 -0.0217 1.0000 0.0666
-7.750 -0.7979 0.01226 0.00607 -0.0211 1.0000 0.0778
-7.500 -0.7733 0.01189 0.00575 -0.0204 1.0000 0.0879
-7.250 -0.7483 0.01158 0.00546 -0.0198 1.0000 0.0979
-7.000 -0.7235 0.01128 0.00517 -0.0192 1.0000 0.1080
-6.750 -0.6988 0.01096 0.00489 -0.0185 1.0000 0.1173
-6.500 -0.6739 0.01069 0.00464 -0.0178 1.0000 0.1263
-6.000 -0.6239 0.01021 0.00423 -0.0165 1.0000 0.1452
-5.750 -0.5989 0.01000 0.00404 -0.0158 1.0000 0.1537
-5.500 -0.5739 0.00984 0.00389 -0.0150 1.0000 0.1625
-5.250 -0.5493 0.00963 0.00373 -0.0143 1.0000 0.1711
-5.000 -0.5244 0.00951 0.00359 -0.0135 1.0000 0.1789
-4.750 -0.5002 0.00933 0.00347 -0.0127 1.0000 0.1883
-4.500 -0.4761 0.00921 0.00336 -0.0118 1.0000 0.1965
-4.250 -0.4518 0.00907 0.00327 -0.0110 0.9998 0.2044
-4.000 -0.4101 0.00894 0.00316 -0.0138 0.9944 0.2137
-3.750 -0.3684 0.00881 0.00305 -0.0165 0.9866 0.2233
-3.500 -0.3266 0.00863 0.00291 -0.0192 0.9762 0.2321
-3.250 -0.2856 0.00850 0.00278 -0.0217 0.9616 0.2410
-3.000 -0.2448 0.00830 0.00263 -0.0241 0.9399 0.2511
-2.750 -0.2084 0.00823 0.00249 -0.0254 0.9034 0.2605
-2.500 -0.1808 0.00816 0.00235 -0.0248 0.8600 0.2692
-2.250 -0.1547 0.00820 0.00224 -0.0240 0.8230 0.2768
-2.000 -0.1287 0.00815 0.00213 -0.0233 0.7934 0.2862
-1.750 -0.1021 0.00814 0.00204 -0.0227 0.7670 0.2958
-1.500 -0.0755 0.00810 0.00196 -0.0221 0.7403 0.3077
-1.250 -0.0489 0.00806 0.00189 -0.0216 0.7163 0.3224
-1.000 -0.0221 0.00799 0.00182 -0.0211 0.6921 0.3413
-0.750 0.0045 0.00792 0.00177 -0.0206 0.6674 0.3669
-0.500 0.0310 0.00781 0.00173 -0.0201 0.6435 0.4031
-0.250 0.0574 0.00768 0.00171 -0.0197 0.6201 0.4530
0.000 0.0836 0.00758 0.00171 -0.0191 0.5960 0.5056
0.250 0.1100 0.00752 0.00172 -0.0186 0.5691 0.5508
0.500 0.1363 0.00750 0.00174 -0.0180 0.5407 0.5903
0.750 0.1625 0.00752 0.00177 -0.0174 0.5113 0.6286
1.000 0.1887 0.00755 0.00182 -0.0168 0.4796 0.6642
1.250 0.2147 0.00763 0.00187 -0.0162 0.4440 0.6962
1.500 0.2404 0.00775 0.00193 -0.0155 0.4006 0.7273
1.750 0.2655 0.00794 0.00202 -0.0148 0.3482 0.7594
2.000 0.2901 0.00813 0.00214 -0.0139 0.3035 0.7950
2.250 0.3145 0.00828 0.00228 -0.0129 0.2762 0.8342
2.500 0.3392 0.00837 0.00241 -0.0118 0.2584 0.8769
2.750 0.3678 0.00849 0.00256 -0.0116 0.2440 0.9252
3.000 0.4140 0.00868 0.00271 -0.0152 0.2299 0.9693
3.250 0.4570 0.00886 0.00285 -0.0183 0.2190 1.0000
3.500 0.4820 0.00911 0.00301 -0.0177 0.2106 1.0000
3.750 0.5083 0.00925 0.00314 -0.0172 0.2040 1.0000
4.000 0.5340 0.00948 0.00330 -0.0166 0.1970 1.0000
4.250 0.5604 0.00965 0.00346 -0.0161 0.1909 1.0000
4.500 0.5868 0.00983 0.00362 -0.0157 0.1851 1.0000
4.750 0.6125 0.01013 0.00385 -0.0151 0.1787 1.0000
5.000 0.6396 0.01024 0.00399 -0.0148 0.1741 1.0000
5.250 0.6661 0.01044 0.00417 -0.0144 0.1693 1.0000
5.500 0.6919 0.01075 0.00442 -0.0139 0.1641 1.0000
5.750 0.7187 0.01093 0.00463 -0.0135 0.1606 1.0000
6.000 0.7455 0.01110 0.00483 -0.0131 0.1562 1.0000
6.250 0.7716 0.01136 0.00504 -0.0127 0.1510 1.0000
6.500 0.7980 0.01158 0.00528 -0.0123 0.1461 1.0000
6.750 0.8248 0.01175 0.00547 -0.0119 0.1414 1.0000
7.000 0.8508 0.01202 0.00571 -0.0115 0.1362 1.0000
7.250 0.8772 0.01225 0.00597 -0.0111 0.1316 1.0000
7.500 0.9037 0.01243 0.00617 -0.0107 0.1259 1.0000
7.750 0.9294 0.01274 0.00645 -0.0103 0.1198 1.0000
8.000 0.9559 0.01293 0.00667 -0.0099 0.1137 1.0000
8.250 0.9812 0.01326 0.00698 -0.0094 0.1072 1.0000
8.500 1.0071 0.01352 0.00726 -0.0090 0.1003 1.0000
8.750 1.0322 0.01388 0.00760 -0.0085 0.0934 1.0000
9.000 1.0569 0.01429 0.00798 -0.0080 0.0863 1.0000
9.250 1.0816 0.01466 0.00838 -0.0074 0.0808 1.0000
9.500 1.1054 0.01515 0.00884 -0.0068 0.0756 1.0000
9.750 1.1298 0.01555 0.00929 -0.0062 0.0717 1.0000
10.000 1.1532 0.01605 0.00978 -0.0056 0.0672 1.0000
10.250 1.1769 0.01650 0.01027 -0.0050 0.0630 1.0000
10.500 1.1995 0.01706 0.01082 -0.0043 0.0585 1.0000
10.750 1.2225 0.01755 0.01137 -0.0036 0.0543 1.0000
11.000 1.2435 0.01824 0.01205 -0.0028 0.0492 1.0000
11.250 1.2645 0.01892 0.01274 -0.0019 0.0429 1.0000
11.500 1.2850 0.01963 0.01346 -0.0010 0.0362 1.0000
11.750 1.3042 0.02042 0.01426 0.0000 0.0306 1.0000
12.250 1.3386 0.02223 0.01613 0.0025 0.0254 1.0000
12.500 1.3534 0.02324 0.01720 0.0039 0.0241 1.0000
12.750 1.3643 0.02447 0.01848 0.0057 0.0231 1.0000
13.000 1.3757 0.02553 0.01965 0.0074 0.0224 1.0000
13.250 1.3815 0.02666 0.02088 0.0099 0.0219 1.0000
13.500 1.3840 0.02792 0.02224 0.0125 0.0215 1.0000
13.750 1.3832 0.02951 0.02394 0.0147 0.0210 1.0000
14.000 1.3799 0.03153 0.02606 0.0162 0.0207 1.0000
14.250 1.3738 0.03416 0.02880 0.0168 0.0204 1.0000
14.500 1.3667 0.03735 0.03210 0.0164 0.0202 1.0000
14.750 1.3560 0.04144 0.03632 0.0149 0.0200 1.0000
15.000 1.3397 0.04675 0.04177 0.0123 0.0197 1.0000
15.250 1.3222 0.05270 0.04785 0.0091 0.0196 1.0000
15.500 1.3065 0.05866 0.05396 0.0058 0.0196 1.0000
15.750 1.2885 0.06515 0.06057 0.0023 0.0195 1.0000
16.000 1.2714 0.07170 0.06727 -0.0013 0.0195 1.0000
16.250 1.2521 0.07869 0.07438 -0.0051 0.0194 1.0000
16.500 1.2348 0.08542 0.08124 -0.0088 0.0194 1.0000
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Polar data table (+)
Polar graphs
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