EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 500,000 Max Cl/Cd: 124.74 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e393-il-500000.txt Download as CSV file: xf-e393-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3248 0.09804 0.09590 -0.0422 1.0000 0.0177
-9.250 -0.3266 0.09531 0.09319 -0.0420 1.0000 0.0182
-9.000 -0.3305 0.09264 0.09056 -0.0415 1.0000 0.0187
-8.750 -0.3276 0.08880 0.08675 -0.0438 0.9990 0.0193
-8.500 -0.3131 0.08291 0.08087 -0.0509 0.9958 0.0205
-8.250 -0.2954 0.07613 0.07410 -0.0603 0.9909 0.0219
-6.750 -0.2061 0.02185 0.01763 -0.1199 0.9201 0.0145
-6.500 -0.1796 0.01858 0.01384 -0.1209 0.9063 0.0141
-6.250 -0.1523 0.01657 0.01145 -0.1212 0.8915 0.0144
-6.000 -0.1252 0.01532 0.00992 -0.1212 0.8762 0.0150
-5.750 -0.0983 0.01454 0.00891 -0.1211 0.8610 0.0155
-5.500 -0.0737 0.01287 0.00700 -0.1208 0.8463 0.0164
-5.250 -0.0477 0.01213 0.00614 -0.1206 0.8323 0.0178
-5.000 -0.0209 0.01179 0.00569 -0.1205 0.8190 0.0199
-4.750 0.0061 0.01138 0.00516 -0.1203 0.8066 0.0218
-4.500 0.0329 0.01052 0.00417 -0.1203 0.7953 0.0262
-4.250 0.0604 0.01022 0.00376 -0.1203 0.7847 0.0315
-4.000 0.0880 0.00986 0.00331 -0.1203 0.7745 0.0403
-3.750 0.1159 0.00949 0.00296 -0.1204 0.7648 0.0582
-3.500 0.1436 0.00910 0.00268 -0.1207 0.7560 0.1029
-3.250 0.1714 0.00875 0.00249 -0.1209 0.7473 0.1619
-3.000 0.1994 0.00840 0.00233 -0.1213 0.7392 0.2331
-2.750 0.2273 0.00807 0.00219 -0.1216 0.7316 0.3190
-2.500 0.2553 0.00781 0.00215 -0.1219 0.7239 0.4024
-2.250 0.2833 0.00770 0.00215 -0.1220 0.7171 0.4714
-2.000 0.3115 0.00765 0.00214 -0.1221 0.7100 0.5113
-1.750 0.3396 0.00765 0.00212 -0.1221 0.7034 0.5369
-1.500 0.3678 0.00765 0.00211 -0.1221 0.6968 0.5580
-1.250 0.3959 0.00766 0.00211 -0.1221 0.6906 0.5812
-1.000 0.4240 0.00767 0.00212 -0.1222 0.6846 0.6016
-0.750 0.4521 0.00767 0.00213 -0.1222 0.6782 0.6203
-0.500 0.4801 0.00772 0.00215 -0.1222 0.6728 0.6396
-0.250 0.5081 0.00771 0.00218 -0.1222 0.6667 0.6588
0.000 0.5360 0.00773 0.00221 -0.1222 0.6611 0.6777
0.250 0.5639 0.00775 0.00226 -0.1222 0.6555 0.6984
0.500 0.5915 0.00775 0.00231 -0.1221 0.6498 0.7200
1.000 0.6463 0.00777 0.00243 -0.1219 0.6388 0.7686
1.250 0.6730 0.00778 0.00249 -0.1216 0.6335 0.7956
1.500 0.6992 0.00780 0.00258 -0.1211 0.6282 0.8254
1.750 0.7240 0.00777 0.00265 -0.1204 0.6225 0.8599
2.000 0.7460 0.00775 0.00269 -0.1189 0.6173 0.9025
2.250 0.7713 0.00764 0.00267 -0.1181 0.6113 0.9830
2.500 0.8005 0.00772 0.00273 -0.1185 0.6048 1.0000
2.750 0.8289 0.00783 0.00281 -0.1187 0.5980 1.0000
3.000 0.8572 0.00792 0.00288 -0.1189 0.5913 1.0000
3.250 0.8852 0.00803 0.00297 -0.1190 0.5846 1.0000
3.500 0.9130 0.00812 0.00307 -0.1191 0.5769 1.0000
3.750 0.9406 0.00823 0.00317 -0.1191 0.5697 1.0000
4.000 0.9681 0.00834 0.00328 -0.1191 0.5621 1.0000
4.250 0.9954 0.00844 0.00339 -0.1191 0.5535 1.0000
4.500 1.0223 0.00859 0.00352 -0.1190 0.5450 1.0000
4.750 1.0494 0.00868 0.00366 -0.1189 0.5358 1.0000
5.000 1.0762 0.00881 0.00380 -0.1188 0.5265 1.0000
5.250 1.1023 0.00897 0.00395 -0.1185 0.5154 1.0000
5.500 1.1284 0.00912 0.00412 -0.1183 0.5036 1.0000
5.750 1.1545 0.00927 0.00430 -0.1180 0.4913 1.0000
6.000 1.1800 0.00946 0.00450 -0.1177 0.4771 1.0000
6.250 1.2046 0.00969 0.00471 -0.1172 0.4600 1.0000
6.500 1.2281 0.00999 0.00497 -0.1165 0.4340 1.0000
6.750 1.2491 0.01044 0.00528 -0.1154 0.3953 1.0000
7.000 1.2671 0.01113 0.00573 -0.1139 0.3443 1.0000
7.250 1.2826 0.01204 0.00634 -0.1121 0.2879 1.0000
7.500 1.2966 0.01305 0.00705 -0.1101 0.2346 1.0000
7.750 1.3106 0.01404 0.00777 -0.1081 0.1875 1.0000
8.000 1.3244 0.01498 0.00852 -0.1061 0.1490 1.0000
8.250 1.3382 0.01587 0.00924 -0.1041 0.1181 1.0000
8.500 1.3517 0.01672 0.00996 -0.1020 0.0941 1.0000
8.750 1.3620 0.01757 0.01070 -0.0993 0.0736 1.0000
9.000 1.3709 0.01846 0.01149 -0.0965 0.0556 1.0000
9.250 1.3780 0.01947 0.01241 -0.0935 0.0386 1.0000
9.500 1.3786 0.02091 0.01370 -0.0897 0.0192 1.0000
9.750 1.3814 0.02231 0.01509 -0.0865 0.0126 1.0000
10.000 1.3875 0.02357 0.01643 -0.0838 0.0107 1.0000
10.250 1.3954 0.02476 0.01773 -0.0816 0.0098 1.0000
10.500 1.4015 0.02615 0.01919 -0.0794 0.0089 1.0000
10.750 1.4042 0.02787 0.02101 -0.0770 0.0084 1.0000
11.000 1.4035 0.02999 0.02326 -0.0747 0.0080 1.0000
11.250 1.4051 0.03205 0.02543 -0.0728 0.0078 1.0000
11.500 1.4089 0.03402 0.02751 -0.0713 0.0076 1.0000
11.750 1.4111 0.03622 0.02982 -0.0699 0.0075 1.0000
12.000 1.4129 0.03857 0.03228 -0.0687 0.0073 1.0000
12.250 1.4137 0.04110 0.03493 -0.0676 0.0072 1.0000
12.500 1.4142 0.04375 0.03770 -0.0667 0.0070 1.0000
12.750 1.4152 0.04645 0.04051 -0.0659 0.0069 1.0000
13.000 1.4155 0.04929 0.04346 -0.0652 0.0068 1.0000
13.250 1.4168 0.05211 0.04640 -0.0647 0.0066 1.0000
13.500 1.4186 0.05493 0.04935 -0.0644 0.0064 1.0000
13.750 1.4195 0.05794 0.05246 -0.0643 0.0062 1.0000
14.000 1.4203 0.06106 0.05568 -0.0642 0.0061 1.0000
14.250 1.4202 0.06437 0.05911 -0.0643 0.0059 1.0000
14.500 1.4193 0.06788 0.06275 -0.0645 0.0059 1.0000
14.750 1.4180 0.07155 0.06654 -0.0648 0.0058 1.0000
15.000 1.4161 0.07542 0.07054 -0.0652 0.0057 1.0000
15.250 1.4139 0.07942 0.07468 -0.0658 0.0057 1.0000
15.500 1.4104 0.08370 0.07910 -0.0667 0.0056 1.0000
15.750 1.4065 0.08820 0.08375 -0.0677 0.0056 1.0000
16.000 1.4013 0.09300 0.08870 -0.0690 0.0055 1.0000
16.250 1.3951 0.09809 0.09396 -0.0706 0.0055 1.0000
16.500 1.3878 0.10350 0.09954 -0.0726 0.0055 1.0000
16.750 1.3796 0.10924 0.10545 -0.0749 0.0055 1.0000
17.000 1.3701 0.11537 0.11175 -0.0776 0.0055 1.0000
17.250 1.3603 0.12172 0.11828 -0.0807 0.0055 1.0000
17.500 1.3496 0.12845 0.12518 -0.0842 0.0055 1.0000
17.750 1.3384 0.13552 0.13243 -0.0882 0.0055 1.0000
18.000 1.3263 0.14302 0.14011 -0.0927 0.0055 1.0000
18.250 1.3134 0.15103 0.14830 -0.0978 0.0056 1.0000
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