EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 50,000 Max Cl/Cd: 28.18 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e395-il-50000-n5.txt Download as CSV file: xf-e395-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 395 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3388 0.11948 0.11300 -0.0466 1.0000 0.0481
-9.500 -0.3568 0.11465 0.10837 -0.0440 1.0000 0.0481
-9.250 -0.3670 0.11223 0.10604 -0.0426 1.0000 0.0481
-9.000 -0.3764 0.11002 0.10392 -0.0411 1.0000 0.0480
-8.750 -0.3691 0.10476 0.09868 -0.0458 0.9945 0.0480
-8.500 -0.3543 0.10201 0.09593 -0.0478 0.9891 0.0498
-8.250 -0.3433 0.09843 0.09234 -0.0513 0.9834 0.0522
-8.000 -0.3411 0.09407 0.08801 -0.0548 0.9757 0.0534
-7.750 -0.3425 0.08936 0.08335 -0.0588 0.9678 0.0543
-7.500 -0.3451 0.08394 0.07798 -0.0637 0.9594 0.0547
-7.250 -0.3489 0.07719 0.07127 -0.0702 0.9495 0.0549
-7.000 -0.3504 0.06700 0.06103 -0.0821 0.9399 0.0547
-6.750 -0.3433 0.05519 0.04868 -0.0974 0.9319 0.0557
-6.500 -0.3259 0.04743 0.04012 -0.1062 0.9246 0.0595
-6.250 -0.2977 0.04490 0.03732 -0.1094 0.9196 0.0657
-6.000 -0.2618 0.04125 0.03311 -0.1146 0.9163 0.0743
-5.750 -0.2361 0.03856 0.02980 -0.1168 0.9101 0.0836
-5.500 -0.2047 0.03710 0.02811 -0.1189 0.9054 0.0944
-5.250 -0.1684 0.03561 0.02633 -0.1216 0.9021 0.1074
-5.000 -0.1438 0.03465 0.02520 -0.1220 0.8960 0.1191
-4.750 -0.1125 0.03369 0.02402 -0.1235 0.8912 0.1344
-4.500 -0.0757 0.03275 0.02278 -0.1259 0.8877 0.1537
-4.250 -0.0501 0.03224 0.02214 -0.1262 0.8819 0.1704
-4.000 -0.0214 0.03182 0.02168 -0.1269 0.8766 0.1895
-3.750 0.0140 0.03135 0.02102 -0.1287 0.8728 0.2142
-3.500 0.0387 0.03118 0.02082 -0.1287 0.8669 0.2348
-3.250 0.0674 0.03098 0.02049 -0.1294 0.8615 0.2592
-3.000 0.1023 0.03073 0.02019 -0.1309 0.8577 0.2863
-2.750 0.1263 0.03074 0.02012 -0.1307 0.8516 0.3108
-2.500 0.1548 0.03070 0.01999 -0.1312 0.8461 0.3373
-2.250 0.1899 0.03054 0.01978 -0.1326 0.8424 0.3671
-2.000 0.2114 0.03072 0.01994 -0.1319 0.8358 0.3924
-1.750 0.2401 0.03074 0.01992 -0.1323 0.8305 0.4218
-1.500 0.2752 0.03062 0.01978 -0.1336 0.8270 0.4548
-1.250 0.2934 0.03096 0.02012 -0.1324 0.8195 0.4826
-1.000 0.3226 0.03098 0.02016 -0.1327 0.8145 0.5159
-0.750 0.3571 0.03085 0.02007 -0.1336 0.8113 0.5540
-0.500 0.3704 0.03134 0.02063 -0.1316 0.8028 0.5852
-0.250 0.3996 0.03130 0.02066 -0.1316 0.7983 0.6274
0.000 0.4215 0.03146 0.02091 -0.1305 0.7927 0.6712
0.250 0.4378 0.03171 0.02128 -0.1284 0.7856 0.7187
0.500 0.4622 0.03144 0.02115 -0.1269 0.7817 0.7851
1.000 0.5019 0.03182 0.02152 -0.1246 0.7678 1.0000
1.250 0.5272 0.03246 0.02199 -0.1251 0.7609 1.0000
1.500 0.5549 0.03297 0.02235 -0.1257 0.7546 1.0000
1.750 0.5930 0.03307 0.02231 -0.1275 0.7511 1.0000
2.000 0.6062 0.03413 0.02329 -0.1262 0.7414 1.0000
2.250 0.6410 0.03430 0.02337 -0.1274 0.7371 1.0000
2.500 0.6572 0.03526 0.02429 -0.1265 0.7283 1.0000
2.750 0.6881 0.03556 0.02454 -0.1271 0.7230 1.0000
3.250 0.7347 0.03684 0.02576 -0.1267 0.7087 1.0000
3.500 0.7721 0.03676 0.02569 -0.1278 0.7053 1.0000
3.750 0.7808 0.03811 0.02707 -0.1260 0.6941 1.0000
4.000 0.8179 0.03798 0.02695 -0.1270 0.6904 1.0000
4.250 0.8267 0.03936 0.02839 -0.1253 0.6791 1.0000
4.500 0.8639 0.03914 0.02821 -0.1261 0.6753 1.0000
4.750 0.8726 0.04054 0.02966 -0.1243 0.6637 1.0000
5.000 0.9106 0.04017 0.02939 -0.1251 0.6600 1.0000
5.250 0.9188 0.04160 0.03089 -0.1233 0.6479 1.0000
5.500 0.9587 0.04100 0.03039 -0.1241 0.6444 1.0000
5.750 0.9660 0.04246 0.03194 -0.1221 0.6318 1.0000
6.000 0.9783 0.04365 0.03324 -0.1207 0.6203 1.0000
6.250 1.0158 0.04297 0.03270 -0.1209 0.6156 1.0000
6.500 1.0258 0.04424 0.03408 -0.1192 0.6031 1.0000
7.000 1.0782 0.04423 0.03439 -0.1178 0.5860 1.0000
7.250 1.0899 0.04529 0.03559 -0.1161 0.5732 1.0000
7.500 1.1061 0.04596 0.03641 -0.1147 0.5612 1.0000
7.750 1.1488 0.04438 0.03506 -0.1146 0.5551 1.0000
8.000 1.1620 0.04514 0.03599 -0.1128 0.5415 1.0000
8.250 1.1778 0.04568 0.03670 -0.1112 0.5279 1.0000
8.500 1.1958 0.04597 0.03718 -0.1096 0.5143 1.0000
8.750 1.2158 0.04605 0.03747 -0.1081 0.5003 1.0000
9.000 1.2365 0.04599 0.03760 -0.1065 0.4853 1.0000
9.250 1.2573 0.04586 0.03765 -0.1049 0.4689 1.0000
9.500 1.2806 0.04544 0.03741 -0.1032 0.4510 1.0000
9.750 1.2926 0.04612 0.03823 -0.1012 0.4304 1.0000
10.000 1.3061 0.04666 0.03888 -0.0992 0.4078 1.0000
10.250 1.3172 0.04747 0.03976 -0.0972 0.3834 1.0000
10.500 1.3285 0.04827 0.04056 -0.0952 0.3571 1.0000
10.750 1.3350 0.04964 0.04191 -0.0931 0.3301 1.0000
11.000 1.3367 0.05163 0.04391 -0.0912 0.3030 1.0000
11.250 1.3372 0.05388 0.04610 -0.0894 0.2768 1.0000
11.500 1.3360 0.05640 0.04853 -0.0877 0.2518 1.0000
11.750 1.3330 0.05926 0.05134 -0.0863 0.2282 1.0000
12.000 1.3294 0.06238 0.05441 -0.0851 0.2061 1.0000
12.250 1.3250 0.06572 0.05770 -0.0842 0.1858 1.0000
12.500 1.3203 0.06922 0.06111 -0.0834 0.1678 1.0000
12.750 1.3163 0.07288 0.06478 -0.0829 0.1503 1.0000
13.000 1.3122 0.07664 0.06855 -0.0826 0.1348 1.0000
13.250 1.3083 0.08050 0.07241 -0.0825 0.1211 1.0000
13.500 1.3050 0.08439 0.07633 -0.0825 0.1091 1.0000
13.750 1.3017 0.08834 0.08023 -0.0826 0.0988 1.0000
14.000 1.3002 0.09222 0.08421 -0.0828 0.0891 1.0000
14.250 1.2993 0.09609 0.08820 -0.0831 0.0806 1.0000
14.500 1.2986 0.09982 0.09189 -0.0835 0.0740 1.0000
14.750 1.2987 0.10377 0.09607 -0.0840 0.0672 1.0000
15.000 1.2994 0.10741 0.09970 -0.0845 0.0621 1.0000
15.250 1.2992 0.11159 0.10418 -0.0853 0.0572 1.0000
15.500 1.3001 0.11519 0.10776 -0.0862 0.0532 1.0000
15.750 1.2990 0.11973 0.11258 -0.0874 0.0499 1.0000
16.000 1.2960 0.12463 0.11775 -0.0891 0.0470 1.0000
16.250 1.2948 0.12892 0.12213 -0.0908 0.0445 1.0000
16.500 1.2949 0.13307 0.12637 -0.0924 0.0423 1.0000
16.750 1.2849 0.13990 0.13355 -0.0959 0.0412 1.0000
17.000 1.2731 0.14737 0.14132 -0.1001 0.0405 1.0000
17.250 1.2584 0.15593 0.15012 -0.1054 0.0401 1.0000
17.500 1.2404 0.16598 0.16040 -0.1120 0.0402 1.0000
17.750 1.2199 0.17777 0.17234 -0.1198 0.0407 1.0000
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