EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 100,000 Max Cl/Cd: 44.59 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ec863914-il-100000-n5.txt Download as CSV file: xf-ec863914-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5061 0.09674 0.09195 -0.0541 0.9951 0.0154
-10.500 -0.5200 0.08943 0.08455 -0.0589 0.9931 0.0153
-10.250 -0.5338 0.08255 0.07758 -0.0642 0.9906 0.0152
-10.000 -0.5503 0.07596 0.07087 -0.0694 0.9881 0.0151
-9.750 -0.5661 0.07042 0.06519 -0.0738 0.9850 0.0150
-9.500 -0.5830 0.06637 0.06100 -0.0754 0.9810 0.0149
-9.250 -0.5990 0.06284 0.05731 -0.0767 0.9766 0.0149
-9.000 -0.6108 0.05959 0.05387 -0.0780 0.9724 0.0148
-8.750 -0.6164 0.05609 0.05012 -0.0793 0.9675 0.0147
-8.500 -0.6098 0.05232 0.04601 -0.0822 0.9638 0.0146
-8.250 -0.5942 0.04888 0.04221 -0.0850 0.9612 0.0145
-8.000 -0.5844 0.04616 0.03920 -0.0850 0.9572 0.0144
-7.750 -0.5652 0.04367 0.03641 -0.0861 0.9541 0.0143
-7.500 -0.5413 0.04146 0.03393 -0.0875 0.9518 0.0142
-7.250 -0.5146 0.03957 0.03179 -0.0888 0.9500 0.0141
-7.000 -0.4926 0.03797 0.03002 -0.0890 0.9471 0.0141
-6.750 -0.4704 0.03651 0.02839 -0.0891 0.9438 0.0141
-6.500 -0.4435 0.03522 0.02696 -0.0901 0.9412 0.0141
-6.250 -0.4125 0.03401 0.02560 -0.0921 0.9390 0.0142
-6.000 -0.3779 0.03290 0.02431 -0.0948 0.9372 0.0142
-5.750 -0.3430 0.03188 0.02307 -0.0975 0.9353 0.0144
-5.500 -0.3162 0.03103 0.02205 -0.0985 0.9315 0.0145
-5.250 -0.2830 0.03029 0.02105 -0.1006 0.9287 0.0147
-5.000 -0.2478 0.02968 0.02022 -0.1028 0.9264 0.0150
-4.750 -0.2113 0.02923 0.01960 -0.1051 0.9244 0.0154
-4.500 -0.1733 0.02882 0.01903 -0.1076 0.9228 0.0163
-4.250 -0.1485 0.02845 0.01857 -0.1076 0.9181 0.0173
-4.000 -0.1153 0.02808 0.01816 -0.1091 0.9149 0.0227
-3.750 -0.0751 0.02692 0.01793 -0.1132 0.9134 0.1849
-3.500 -0.0391 0.02695 0.01782 -0.1150 0.9112 0.1996
-3.250 -0.0115 0.02685 0.01779 -0.1155 0.9066 0.2311
-3.000 0.0208 0.02676 0.01775 -0.1168 0.9028 0.2549
-2.750 0.0570 0.02671 0.01772 -0.1188 0.9002 0.2756
-2.500 0.0916 0.02654 0.01774 -0.1208 0.8968 0.3161
-2.250 0.1219 0.02642 0.01771 -0.1219 0.8918 0.3472
-2.000 0.1617 0.02611 0.01782 -0.1249 0.8893 0.4303
-1.750 0.1761 0.02625 0.01873 -0.1213 0.8833 0.5437
-1.500 0.1990 0.02660 0.01916 -0.1195 0.8780 0.5991
-1.250 0.2311 0.02682 0.01926 -0.1203 0.8734 0.6318
-1.000 0.2619 0.02701 0.01934 -0.1210 0.8674 0.6553
-0.750 0.2963 0.02714 0.01939 -0.1218 0.8642 0.6714
-0.500 0.3181 0.02734 0.01952 -0.1208 0.8558 0.6846
-0.250 0.3512 0.02736 0.01949 -0.1212 0.8523 0.6962
0.000 0.3692 0.02749 0.01962 -0.1191 0.8430 0.7048
0.250 0.4057 0.02735 0.01942 -0.1203 0.8394 0.7153
0.500 0.4241 0.02738 0.01946 -0.1183 0.8291 0.7232
0.750 0.4496 0.02729 0.01935 -0.1176 0.8201 0.7312
1.000 0.4813 0.02695 0.01901 -0.1176 0.8139 0.7393
1.250 0.5009 0.02690 0.01898 -0.1157 0.8031 0.7481
1.500 0.5337 0.02645 0.01855 -0.1156 0.7982 0.7603
1.750 0.5495 0.02640 0.01855 -0.1127 0.7861 0.7710
2.000 0.5682 0.02619 0.01839 -0.1103 0.7747 0.7799
2.250 0.5990 0.02573 0.01794 -0.1103 0.7657 0.7894
2.500 0.6211 0.02525 0.01750 -0.1083 0.7550 0.7958
3.000 0.6789 0.02459 0.01690 -0.1081 0.7284 0.8061
3.250 0.7100 0.02411 0.01644 -0.1082 0.7143 0.8087
3.500 0.7445 0.02360 0.01596 -0.1090 0.6990 0.8111
3.750 0.7826 0.02304 0.01538 -0.1104 0.6814 0.8135
4.000 0.8212 0.02258 0.01490 -0.1120 0.6590 0.8158
4.250 0.8633 0.02211 0.01435 -0.1143 0.6316 0.8176
4.500 0.9034 0.02185 0.01399 -0.1163 0.5983 0.8194
4.750 0.9365 0.02175 0.01376 -0.1169 0.5624 0.8211
5.000 0.9658 0.02191 0.01376 -0.1171 0.5251 0.8229
5.250 0.9917 0.02227 0.01397 -0.1169 0.4880 0.8245
5.500 1.0153 0.02277 0.01431 -0.1165 0.4541 0.8262
5.750 1.0377 0.02334 0.01475 -0.1159 0.4239 0.8281
6.000 1.0601 0.02394 0.01527 -0.1154 0.3973 0.8303
6.250 1.0827 0.02459 0.01584 -0.1151 0.3736 0.8323
6.500 1.1057 0.02528 0.01649 -0.1148 0.3524 0.8341
6.750 1.1263 0.02592 0.01710 -0.1141 0.3348 0.8355
7.000 1.1471 0.02657 0.01773 -0.1133 0.3195 0.8370
7.250 1.1687 0.02720 0.01839 -0.1127 0.3066 0.8388
7.500 1.1909 0.02784 0.01911 -0.1122 0.2955 0.8408
7.750 1.2132 0.02855 0.01984 -0.1118 0.2857 0.8430
8.000 1.2362 0.02925 0.02062 -0.1116 0.2760 0.8450
8.250 1.2601 0.02997 0.02143 -0.1115 0.2674 0.8468
8.500 1.2842 0.03074 0.02226 -0.1114 0.2601 0.8486
8.750 1.3077 0.03144 0.02309 -0.1111 0.2537 0.8502
9.000 1.3301 0.03216 0.02398 -0.1107 0.2474 0.8519
9.250 1.3477 0.03296 0.02491 -0.1096 0.2380 0.8540
9.500 1.3590 0.03387 0.02590 -0.1077 0.2254 0.8563
9.750 1.3701 0.03487 0.02697 -0.1060 0.2126 0.8589
10.000 1.3837 0.03588 0.02813 -0.1047 0.2014 0.8614
10.250 1.3916 0.03707 0.02940 -0.1027 0.1856 0.8636
10.500 1.3983 0.03832 0.03074 -0.1007 0.1612 0.8658
11.000 1.3924 0.04344 0.03506 -0.0958 0.0522 0.8697
11.250 1.3856 0.04689 0.03833 -0.0932 0.0266 0.8715
11.500 1.3848 0.04982 0.04139 -0.0912 0.0193 0.8735
11.750 1.3833 0.05288 0.04460 -0.0895 0.0163 0.8755
12.000 1.3825 0.05573 0.04767 -0.0879 0.0149 0.8776
12.250 1.3798 0.05885 0.05104 -0.0865 0.0138 0.8799
12.500 1.3752 0.06236 0.05479 -0.0854 0.0130 0.8824
12.750 1.3686 0.06634 0.05900 -0.0848 0.0124 0.8849
13.000 1.3601 0.07081 0.06371 -0.0847 0.0120 0.8873
13.250 1.3483 0.07593 0.06907 -0.0850 0.0116 0.8895
13.500 1.3347 0.08153 0.07491 -0.0859 0.0114 0.8917
13.750 1.3215 0.08750 0.08110 -0.0875 0.0111 0.8938
14.000 1.3092 0.09374 0.08759 -0.0897 0.0110 0.8959
14.250 1.2959 0.10048 0.09457 -0.0924 0.0107 0.8980
14.500 1.2826 0.10761 0.10192 -0.0957 0.0107 0.9000
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