EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 50,000 Max Cl/Cd: 17.63 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e328-il-50000.txt Download as CSV file: xf-e328-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3686 0.11103 0.10452 -0.0143 1.0000 0.2346
-9.250 -0.3682 0.10792 0.10150 -0.0145 1.0000 0.2455
-9.000 -0.3943 0.10685 0.10059 -0.0162 1.0000 0.2566
-8.750 -0.3588 0.10174 0.09547 -0.0131 1.0000 0.2793
-8.500 -0.3539 0.09890 0.09270 -0.0121 1.0000 0.2985
-8.250 -0.3657 0.09697 0.09091 -0.0113 1.0000 0.3197
-8.000 -0.3469 0.09367 0.08766 -0.0087 1.0000 0.3499
-7.750 -0.3383 0.09107 0.08514 -0.0062 1.0000 0.3825
-7.500 -0.3148 0.08782 0.08193 -0.0030 1.0000 0.4248
-7.250 -0.3196 0.08667 0.08091 0.0006 1.0000 0.4648
-7.000 -0.2729 0.08244 0.07666 0.0031 1.0000 0.5204
-6.750 -0.2624 0.08101 0.07532 0.0071 1.0000 0.5767
-6.500 -0.2177 0.07703 0.07136 0.0079 1.0000 0.6386
-5.750 -0.2669 0.06879 0.06364 0.0090 1.0000 0.5730
-5.500 -0.3326 0.06694 0.06220 0.0119 1.0000 0.5309
-5.250 -0.3764 0.06664 0.06222 0.0184 1.0000 0.5303
-5.000 -0.4150 0.06687 0.06267 0.0254 1.0000 0.5316
-4.750 -0.4566 0.06681 0.06280 0.0318 1.0000 0.5329
-4.500 -0.5094 0.06125 0.05726 0.0233 0.9862 0.4849
-4.250 -0.4408 0.04809 0.04083 -0.0119 0.9621 0.1560
-4.000 -0.3896 0.04435 0.03612 -0.0151 0.9478 0.1256
-3.750 -0.3414 0.04166 0.03248 -0.0176 0.9332 0.1122
-3.500 -0.2949 0.03859 0.02911 -0.0206 0.9189 0.1098
-3.250 -0.2472 0.03659 0.02657 -0.0233 0.9043 0.1120
-3.000 0.1317 0.02677 0.01935 -0.0653 0.9337 1.0000
-2.750 0.1963 0.02597 0.01793 -0.0729 0.9127 1.0000
-2.500 0.2489 0.02540 0.01692 -0.0780 0.8909 1.0000
-2.250 0.2911 0.02506 0.01621 -0.0810 0.8702 1.0000
-2.000 0.3192 0.02512 0.01599 -0.0815 0.8489 1.0000
-1.750 0.3425 0.02532 0.01597 -0.0811 0.8295 1.0000
-1.500 0.3640 0.02560 0.01604 -0.0802 0.8115 1.0000
-1.250 0.3851 0.02593 0.01619 -0.0794 0.7952 1.0000
-1.000 0.4058 0.02633 0.01643 -0.0786 0.7803 1.0000
-0.750 0.4258 0.02675 0.01672 -0.0776 0.7662 1.0000
-0.500 0.4458 0.02717 0.01698 -0.0765 0.7536 1.0000
-0.250 0.4646 0.02767 0.01738 -0.0753 0.7414 1.0000
0.000 0.4811 0.02837 0.01801 -0.0741 0.7289 1.0000
0.250 0.4985 0.02903 0.01858 -0.0728 0.7178 1.0000
0.500 0.5186 0.02948 0.01893 -0.0716 0.7082 1.0000
0.750 0.5321 0.03048 0.01992 -0.0703 0.6969 1.0000
1.000 0.5497 0.03118 0.02056 -0.0690 0.6878 1.0000
1.250 0.5650 0.03205 0.02140 -0.0676 0.6781 1.0000
1.500 0.5775 0.03318 0.02253 -0.0662 0.6691 1.0000
1.750 0.5948 0.03391 0.02322 -0.0648 0.6608 1.0000
2.000 0.6016 0.03544 0.02479 -0.0630 0.6517 1.0000
2.250 0.6197 0.03616 0.02548 -0.0615 0.6442 1.0000
2.500 0.6192 0.03817 0.02754 -0.0592 0.6356 1.0000
2.750 0.6361 0.03898 0.02833 -0.0577 0.6284 1.0000
3.000 0.6282 0.04140 0.03081 -0.0547 0.6206 1.0000
3.250 0.6351 0.04282 0.03224 -0.0525 0.6135 1.0000
3.500 0.6282 0.04504 0.03448 -0.0492 0.6066 1.0000
3.750 0.6050 0.04797 0.03744 -0.0448 0.6001 1.0000
4.000 0.6417 0.04797 0.03743 -0.0447 0.5940 1.0000
4.250 0.5638 0.05308 0.04252 -0.0357 0.5899 1.0000
4.500 0.5085 0.05621 0.04560 -0.0276 0.5879 1.0000
4.750 0.4805 0.05863 0.04798 -0.0227 0.5861 1.0000
5.000 0.4627 0.06089 0.05021 -0.0192 0.5848 1.0000
5.250 0.4497 0.06316 0.05244 -0.0163 0.5842 1.0000
5.500 0.4338 0.06586 0.05511 -0.0141 0.5883 1.0000
5.750 0.4336 0.06842 0.05765 -0.0133 0.5916 1.0000
6.000 0.3304 0.07579 0.06508 -0.0134 0.7239 1.0000
6.250 0.3328 0.07677 0.06604 -0.0117 0.7103 1.0000
6.500 0.3413 0.07841 0.06766 -0.0109 0.6972 1.0000
6.750 0.3552 0.08056 0.06981 -0.0108 0.6860 1.0000
7.000 0.3895 0.08415 0.07343 -0.0130 0.6750 1.0000
7.250 0.3913 0.08515 0.07442 -0.0115 0.6608 1.0000
7.500 0.3960 0.08675 0.07605 -0.0105 0.6477 1.0000
7.750 0.4070 0.08901 0.07832 -0.0104 0.6372 1.0000
8.000 0.4433 0.09304 0.08240 -0.0126 0.6263 1.0000
8.250 0.4410 0.09393 0.08330 -0.0110 0.6125 1.0000
8.500 0.4433 0.09568 0.08507 -0.0102 0.6005 1.0000
8.750 0.4586 0.09855 0.08798 -0.0107 0.5912 1.0000
9.000 0.4881 0.10215 0.09169 -0.0120 0.5786 1.0000
9.250 0.4819 0.10313 0.09268 -0.0106 0.5658 1.0000
9.500 0.4862 0.10540 0.09498 -0.0103 0.5550 1.0000
9.750 0.5126 0.10927 0.09893 -0.0116 0.5453 1.0000
10.000 0.5195 0.11123 0.10095 -0.0113 0.5322 1.0000
10.250 0.5166 0.11310 0.10287 -0.0108 0.5215 1.0000
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Polar data table (+)
Polar graphs
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