EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 500,000 Max Cl/Cd: 117.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e393-il-500000-n5.txt Download as CSV file: xf-e393-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3401 0.10829 0.10598 -0.0410 1.0000 0.0065
-10.500 -0.3416 0.10432 0.10204 -0.0418 1.0000 0.0065
-10.250 -0.3428 0.10071 0.09846 -0.0425 1.0000 0.0065
-10.000 -0.3438 0.09562 0.09339 -0.0446 0.9995 0.0069
-9.750 -0.3389 0.08902 0.08681 -0.0498 0.9970 0.0071
-9.500 -0.3342 0.08351 0.08131 -0.0545 0.9928 0.0070
-9.250 -0.3344 0.07638 0.07420 -0.0605 0.9871 0.0070
-9.000 -0.3376 0.06864 0.06648 -0.0675 0.9791 0.0069
-8.750 -0.4030 0.03189 0.02897 -0.1092 0.9418 0.0064
-8.500 -0.3889 0.02530 0.02163 -0.1145 0.9242 0.0065
-8.250 -0.3654 0.02172 0.01749 -0.1169 0.9078 0.0066
-8.000 -0.3405 0.01952 0.01488 -0.1180 0.8909 0.0067
-7.750 -0.3160 0.01791 0.01289 -0.1183 0.8738 0.0069
-7.500 -0.2915 0.01672 0.01141 -0.1183 0.8570 0.0071
-7.250 -0.2667 0.01580 0.01025 -0.1182 0.8408 0.0072
-7.000 -0.2430 0.01455 0.00875 -0.1181 0.8257 0.0076
-6.750 -0.2176 0.01389 0.00794 -0.1180 0.8118 0.0080
-6.500 -0.1917 0.01340 0.00731 -0.1179 0.7986 0.0085
-6.250 -0.1655 0.01293 0.00669 -0.1178 0.7865 0.0089
-6.000 -0.1390 0.01248 0.00610 -0.1177 0.7749 0.0095
-5.750 -0.1123 0.01205 0.00554 -0.1177 0.7640 0.0101
-5.500 -0.0853 0.01173 0.00511 -0.1177 0.7539 0.0109
-5.250 -0.0584 0.01133 0.00463 -0.1177 0.7443 0.0126
-5.000 -0.0309 0.01103 0.00423 -0.1177 0.7349 0.0142
-4.750 -0.0033 0.01076 0.00385 -0.1178 0.7263 0.0158
-4.500 0.0243 0.01044 0.00347 -0.1179 0.7178 0.0193
-4.250 0.0522 0.01026 0.00321 -0.1179 0.7100 0.0222
-3.750 0.1080 0.00981 0.00271 -0.1182 0.6952 0.0380
-3.500 0.1359 0.00962 0.00251 -0.1183 0.6883 0.0542
-3.250 0.1640 0.00940 0.00234 -0.1185 0.6815 0.0776
-3.000 0.1921 0.00921 0.00218 -0.1187 0.6751 0.1041
-2.750 0.2203 0.00903 0.00205 -0.1189 0.6690 0.1348
-2.500 0.2485 0.00883 0.00193 -0.1192 0.6627 0.1760
-2.250 0.2767 0.00849 0.00182 -0.1196 0.6572 0.2564
-2.000 0.3051 0.00818 0.00176 -0.1200 0.6514 0.3435
-1.750 0.3332 0.00805 0.00172 -0.1202 0.6458 0.3984
-1.500 0.3616 0.00797 0.00170 -0.1204 0.6404 0.4352
-1.250 0.3899 0.00792 0.00170 -0.1205 0.6349 0.4724
-1.000 0.4180 0.00790 0.00170 -0.1206 0.6300 0.5013
-0.750 0.4464 0.00788 0.00171 -0.1207 0.6245 0.5237
-0.500 0.4746 0.00789 0.00172 -0.1208 0.6192 0.5442
-0.250 0.5027 0.00790 0.00174 -0.1209 0.6145 0.5643
0.000 0.5310 0.00790 0.00177 -0.1210 0.6092 0.5821
0.250 0.5590 0.00792 0.00180 -0.1210 0.6041 0.6001
0.500 0.5870 0.00793 0.00185 -0.1211 0.5993 0.6185
0.750 0.6151 0.00794 0.00189 -0.1211 0.5940 0.6369
1.000 0.6429 0.00798 0.00195 -0.1211 0.5889 0.6553
1.250 0.6709 0.00799 0.00201 -0.1212 0.5840 0.6729
1.500 0.6987 0.00802 0.00208 -0.1212 0.5785 0.6902
1.750 0.7261 0.00807 0.00216 -0.1211 0.5735 0.7086
2.000 0.7539 0.00808 0.00224 -0.1211 0.5678 0.7286
2.250 0.7810 0.00812 0.00233 -0.1210 0.5617 0.7500
2.500 0.8079 0.00815 0.00243 -0.1208 0.5548 0.7739
2.750 0.8342 0.00819 0.00253 -0.1204 0.5469 0.8006
3.000 0.8598 0.00820 0.00263 -0.1199 0.5395 0.8311
3.250 0.8836 0.00823 0.00273 -0.1190 0.5318 0.8674
3.500 0.9051 0.00820 0.00282 -0.1175 0.5231 0.9164
3.750 0.9326 0.00823 0.00287 -0.1174 0.5141 1.0000
4.000 0.9598 0.00837 0.00300 -0.1174 0.5047 1.0000
4.250 0.9869 0.00852 0.00313 -0.1173 0.4933 1.0000
4.500 1.0135 0.00869 0.00329 -0.1172 0.4808 1.0000
4.750 1.0400 0.00887 0.00345 -0.1170 0.4686 1.0000
5.000 1.0660 0.00907 0.00363 -0.1168 0.4544 1.0000
5.250 1.0913 0.00932 0.00382 -0.1165 0.4354 1.0000
5.500 1.1159 0.00961 0.00407 -0.1160 0.4138 1.0000
5.750 1.1399 0.00995 0.00433 -0.1155 0.3905 1.0000
6.000 1.1626 0.01038 0.00465 -0.1147 0.3588 1.0000
6.250 1.1833 0.01097 0.00506 -0.1137 0.3197 1.0000
6.500 1.2017 0.01174 0.00558 -0.1124 0.2718 1.0000
6.750 1.2180 0.01266 0.00623 -0.1107 0.2206 1.0000
7.000 1.2344 0.01354 0.00686 -0.1091 0.1750 1.0000
7.250 1.2515 0.01433 0.00746 -0.1076 0.1413 1.0000
7.500 1.2684 0.01508 0.00807 -0.1061 0.1136 1.0000
7.750 1.2843 0.01587 0.00871 -0.1044 0.0882 1.0000
8.000 1.3005 0.01657 0.00933 -0.1027 0.0690 1.0000
8.250 1.3147 0.01734 0.01002 -0.1008 0.0526 1.0000
8.500 1.3277 0.01803 0.01067 -0.0985 0.0412 1.0000
8.750 1.3393 0.01878 0.01138 -0.0961 0.0309 1.0000
9.000 1.3500 0.01960 0.01217 -0.0936 0.0217 1.0000
9.250 1.3599 0.02049 0.01304 -0.0912 0.0144 1.0000
9.500 1.3683 0.02149 0.01404 -0.0886 0.0089 1.0000
9.750 1.3784 0.02244 0.01502 -0.0864 0.0070 1.0000
10.000 1.3883 0.02344 0.01608 -0.0843 0.0059 1.0000
10.250 1.3970 0.02456 0.01729 -0.0822 0.0052 1.0000
10.500 1.4065 0.02569 0.01850 -0.0803 0.0049 1.0000
10.750 1.4156 0.02689 0.01981 -0.0786 0.0046 1.0000
11.000 1.4240 0.02821 0.02122 -0.0769 0.0044 1.0000
11.250 1.4317 0.02965 0.02275 -0.0753 0.0042 1.0000
11.500 1.4384 0.03123 0.02442 -0.0739 0.0040 1.0000
11.750 1.4447 0.03292 0.02621 -0.0725 0.0039 1.0000
12.000 1.4502 0.03475 0.02814 -0.0712 0.0037 1.0000
12.250 1.4546 0.03676 0.03025 -0.0701 0.0036 1.0000
12.500 1.4578 0.03897 0.03257 -0.0690 0.0035 1.0000
12.750 1.4602 0.04133 0.03503 -0.0681 0.0034 1.0000
13.000 1.4613 0.04392 0.03776 -0.0673 0.0033 1.0000
13.250 1.4608 0.04676 0.04072 -0.0667 0.0032 1.0000
13.500 1.4591 0.04984 0.04392 -0.0662 0.0032 1.0000
13.750 1.4554 0.05328 0.04749 -0.0659 0.0031 1.0000
14.000 1.4506 0.05699 0.05133 -0.0658 0.0030 1.0000
14.250 1.4467 0.06071 0.05518 -0.0659 0.0030 1.0000
14.500 1.4454 0.06422 0.05881 -0.0662 0.0029 1.0000
14.750 1.4460 0.06755 0.06227 -0.0666 0.0029 1.0000
15.000 1.4432 0.07147 0.06632 -0.0672 0.0029 1.0000
15.250 1.4410 0.07541 0.07038 -0.0680 0.0028 1.0000
15.500 1.4389 0.07946 0.07456 -0.0689 0.0028 1.0000
15.750 1.4348 0.08393 0.07916 -0.0701 0.0027 1.0000
16.000 1.4309 0.08847 0.08384 -0.0715 0.0027 1.0000
16.250 1.4252 0.09345 0.08895 -0.0731 0.0026 1.0000
16.500 1.4196 0.09853 0.09417 -0.0749 0.0026 1.0000
16.750 1.4129 0.10391 0.09970 -0.0770 0.0026 1.0000
17.000 1.4059 0.10948 0.10541 -0.0793 0.0026 1.0000
17.250 1.3984 0.11526 0.11134 -0.0818 0.0026 1.0000
17.500 1.3907 0.12120 0.11744 -0.0846 0.0025 1.0000
17.750 1.3826 0.12734 0.12372 -0.0877 0.0025 1.0000
18.000 1.3743 0.13362 0.13014 -0.0910 0.0025 1.0000
18.250 1.3659 0.14004 0.13670 -0.0945 0.0025 1.0000
18.500 1.3573 0.14667 0.14348 -0.0983 0.0025 1.0000
18.750 1.3488 0.15337 0.15031 -0.1023 0.0025 1.0000
19.000 1.3404 0.16022 0.15730 -0.1066 0.0025 1.0000
19.250 1.3315 0.16728 0.16449 -0.1110 0.0025 1.0000
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Polar data table (+)
Polar graphs
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