EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 100,000 Max Cl/Cd: 46.65 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e399-il-100000.txt Download as CSV file: xf-e399-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 399 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2758 0.11361 0.10936 -0.0537 0.9823 0.1314
-9.250 -0.3812 0.08200 0.07791 -0.0773 0.9717 0.0649
-9.000 -0.4675 0.06282 0.05845 -0.0976 0.9532 0.0560
-8.750 -0.4761 0.05422 0.04929 -0.1081 0.9426 0.0560
-8.500 -0.4778 0.04857 0.04306 -0.1121 0.9318 0.0565
-8.250 -0.4440 0.04603 0.04059 -0.1154 0.9284 0.0603
-8.000 -0.4374 0.04239 0.03636 -0.1167 0.9182 0.0635
-7.750 -0.4031 0.03966 0.03339 -0.1206 0.9141 0.0704
-7.500 -0.3858 0.03709 0.03030 -0.1215 0.9058 0.0767
-7.250 -0.3527 0.03531 0.02815 -0.1240 0.9006 0.0868
-7.000 -0.3123 0.03361 0.02623 -0.1275 0.8975 0.0991
-6.750 -0.2970 0.03300 0.02572 -0.1262 0.8889 0.1074
-6.500 -0.2613 0.03172 0.02427 -0.1285 0.8842 0.1208
-6.250 -0.2182 0.03046 0.02280 -0.1318 0.8813 0.1378
-6.000 -0.2040 0.03007 0.02243 -0.1303 0.8730 0.1482
-5.750 -0.1695 0.02930 0.02156 -0.1320 0.8683 0.1656
-5.500 -0.1262 0.02838 0.02046 -0.1351 0.8654 0.1881
-5.250 -0.1089 0.02831 0.02037 -0.1339 0.8576 0.2039
-5.000 -0.0780 0.02798 0.02012 -0.1348 0.8524 0.2242
-4.750 -0.0364 0.02753 0.01955 -0.1374 0.8495 0.2508
-4.500 0.0094 0.02706 0.01916 -0.1405 0.8476 0.2774
-4.250 0.0095 0.02766 0.01975 -0.1365 0.8367 0.2900
-4.000 0.0502 0.02736 0.01937 -0.1388 0.8336 0.3173
-3.750 0.0947 0.02701 0.01907 -0.1415 0.8316 0.3435
-3.500 0.0930 0.02784 0.01987 -0.1374 0.8213 0.3562
-3.250 0.1304 0.02766 0.01970 -0.1389 0.8178 0.3803
-3.000 0.1751 0.02730 0.01928 -0.1416 0.8156 0.4072
-2.750 0.1727 0.02832 0.02032 -0.1374 0.8060 0.4191
-2.500 0.2062 0.02826 0.02024 -0.1384 0.8019 0.4416
-2.250 0.2483 0.02795 0.01996 -0.1404 0.7995 0.4649
-2.000 0.2496 0.02896 0.02096 -0.1369 0.7907 0.4784
-1.750 0.2765 0.02915 0.02117 -0.1369 0.7860 0.4981
-1.500 0.3171 0.02889 0.02090 -0.1387 0.7834 0.5217
-1.250 0.3617 0.02850 0.02049 -0.1411 0.7816 0.5464
-1.000 0.3425 0.03032 0.02238 -0.1349 0.7698 0.5548
-0.750 0.3818 0.03009 0.02214 -0.1365 0.7671 0.5796
-0.500 0.4249 0.02969 0.02178 -0.1384 0.7653 0.6034
-0.250 0.4039 0.03180 0.02394 -0.1323 0.7534 0.6148
0.000 0.4395 0.03160 0.02380 -0.1331 0.7506 0.6388
0.250 0.4829 0.03114 0.02336 -0.1350 0.7488 0.6671
0.500 0.4603 0.03355 0.02584 -0.1290 0.7369 0.6811
0.750 0.4937 0.03333 0.02570 -0.1292 0.7340 0.7089
1.000 0.5333 0.03279 0.02522 -0.1301 0.7321 0.7413
1.250 0.5090 0.03542 0.02795 -0.1242 0.7200 0.7611
1.500 0.5398 0.03516 0.02777 -0.1238 0.7171 0.8000
1.750 0.5716 0.03445 0.02715 -0.1227 0.7152 0.8458
2.000 0.5374 0.03702 0.02991 -0.1154 0.7026 0.9011
2.250 0.5896 0.03658 0.02940 -0.1197 0.7000 1.0000
2.500 0.6445 0.03607 0.02874 -0.1238 0.6984 1.0000
2.750 0.6258 0.03931 0.03194 -0.1205 0.6855 1.0000
3.000 0.6716 0.03900 0.03153 -0.1229 0.6832 1.0000
3.250 0.6600 0.04183 0.03435 -0.1200 0.6716 1.0000
3.500 0.6984 0.04181 0.03427 -0.1213 0.6681 1.0000
3.750 0.7454 0.04125 0.03366 -0.1233 0.6661 1.0000
4.000 0.7271 0.04453 0.03693 -0.1199 0.6533 1.0000
4.250 0.7700 0.04412 0.03652 -0.1213 0.6506 1.0000
4.500 0.8118 0.04376 0.03615 -0.1226 0.6479 1.0000
4.750 0.7980 0.04681 0.03921 -0.1196 0.6352 1.0000
5.000 0.8457 0.04595 0.03836 -0.1211 0.6332 1.0000
5.250 0.8287 0.04934 0.04177 -0.1181 0.6199 1.0000
5.500 0.8743 0.04851 0.04096 -0.1193 0.6175 1.0000
5.750 0.9224 0.04740 0.03991 -0.1206 0.6156 1.0000
6.000 0.9066 0.05077 0.04330 -0.1176 0.6017 1.0000
6.250 0.9571 0.04933 0.04191 -0.1189 0.6001 1.0000
6.500 0.9420 0.05273 0.04534 -0.1161 0.5859 1.0000
6.750 0.9374 0.05548 0.04815 -0.1142 0.5737 1.0000
7.000 0.9803 0.05436 0.04710 -0.1147 0.5701 1.0000
7.250 1.0314 0.05243 0.04527 -0.1155 0.5683 1.0000
7.500 1.0884 0.04976 0.04270 -0.1165 0.5674 1.0000
7.750 1.1500 0.04653 0.03960 -0.1178 0.5669 1.0000
8.000 1.0663 0.05625 0.04930 -0.1117 0.5387 1.0000
8.250 1.0802 0.05733 0.05047 -0.1106 0.5292 1.0000
8.500 1.1593 0.05188 0.04518 -0.1118 0.5324 1.0000
8.750 1.2298 0.04707 0.04055 -0.1128 0.5326 1.0000
9.000 1.3236 0.04101 0.03468 -0.1164 0.5323 1.0000
9.250 1.3533 0.03999 0.03379 -0.1155 0.5227 1.0000
9.500 1.4282 0.03605 0.03000 -0.1189 0.5150 1.0000
9.750 1.5066 0.03236 0.02638 -0.1235 0.5031 1.0000
10.000 1.4995 0.03316 0.02730 -0.1183 0.4897 1.0000
10.250 1.5096 0.03316 0.02739 -0.1153 0.4753 1.0000
10.500 1.5231 0.03299 0.02728 -0.1128 0.4595 1.0000
10.750 1.5357 0.03292 0.02725 -0.1102 0.4421 1.0000
11.000 1.5444 0.03319 0.02750 -0.1073 0.4230 1.0000
11.250 1.5375 0.03461 0.02900 -0.1034 0.4037 1.0000
11.500 1.5342 0.03600 0.03039 -0.1001 0.3823 1.0000
11.750 1.5342 0.03733 0.03163 -0.0972 0.3590 1.0000
12.000 1.5258 0.03953 0.03380 -0.0942 0.3357 1.0000
12.250 1.5201 0.04170 0.03584 -0.0915 0.3115 1.0000
12.500 1.5106 0.04443 0.03849 -0.0891 0.2877 1.0000
12.750 1.5018 0.04729 0.04120 -0.0869 0.2646 1.0000
13.000 1.4914 0.05051 0.04435 -0.0850 0.2422 1.0000
13.250 1.4828 0.05373 0.04736 -0.0834 0.2213 1.0000
13.500 1.4729 0.05734 0.05095 -0.0821 0.2010 1.0000
13.750 1.4641 0.06100 0.05451 -0.0811 0.1822 1.0000
14.000 1.4564 0.06466 0.05806 -0.0802 0.1650 1.0000
14.250 1.4502 0.06830 0.06157 -0.0795 0.1490 1.0000
14.500 1.4454 0.07189 0.06504 -0.0789 0.1343 1.0000
14.750 1.4413 0.07553 0.06862 -0.0785 0.1210 1.0000
15.000 1.4380 0.07918 0.07228 -0.0783 0.1092 1.0000
15.250 1.4366 0.08269 0.07579 -0.0780 0.0985 1.0000
15.500 1.4374 0.08594 0.07904 -0.0778 0.0891 1.0000
15.750 1.4406 0.08886 0.08189 -0.0775 0.0809 1.0000
16.000 1.4423 0.09206 0.08512 -0.0775 0.0740 1.0000
16.250 1.4450 0.09528 0.08845 -0.0774 0.0679 1.0000
16.500 1.4564 0.09719 0.09019 -0.0769 0.0617 1.0000
16.750 1.4526 0.10140 0.09471 -0.0775 0.0580 1.0000
17.000 1.4669 0.10299 0.09614 -0.0769 0.0530 1.0000
17.250 1.4616 0.10750 0.10099 -0.0779 0.0504 1.0000
17.500 1.4626 0.11090 0.10450 -0.0786 0.0475 1.0000
17.750 1.4684 0.11391 0.10757 -0.0788 0.0447 1.0000
18.000 1.4598 0.11906 0.11304 -0.0805 0.0432 1.0000
18.250 1.4561 0.12342 0.11760 -0.0819 0.0415 1.0000
18.500 1.4709 0.12492 0.11894 -0.0817 0.0388 1.0000
18.750 1.4531 0.13148 0.12587 -0.0848 0.0383 1.0000
19.000 1.4355 0.13833 0.13305 -0.0884 0.0379 1.0000
19.250 1.4169 0.14564 0.14066 -0.0925 0.0377 1.0000
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