EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 200,000 Max Cl/Cd: 86.42 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e393-il-200000-n5.txt Download as CSV file: xf-e393-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3318 0.09283 0.08945 -0.0453 1.0000 0.0144
-9.000 -0.3363 0.08975 0.08643 -0.0452 1.0000 0.0141
-8.750 -0.3382 0.08576 0.08250 -0.0468 0.9987 0.0139
-8.500 -0.3285 0.07968 0.07644 -0.0532 0.9924 0.0136
-8.250 -0.3210 0.07288 0.06966 -0.0607 0.9841 0.0134
-7.750 -0.3248 0.04671 0.04327 -0.0933 0.9468 0.0122
-7.500 -0.3183 0.03551 0.03129 -0.1040 0.9309 0.0121
-7.250 -0.2975 0.03020 0.02535 -0.1078 0.9191 0.0122
-7.000 -0.2708 0.02671 0.02131 -0.1104 0.9092 0.0126
-6.750 -0.2403 0.02385 0.01794 -0.1126 0.9005 0.0132
-6.500 -0.2106 0.02178 0.01546 -0.1138 0.8898 0.0141
-6.250 -0.1797 0.02051 0.01379 -0.1148 0.8791 0.0154
-6.000 -0.1504 0.01885 0.01192 -0.1159 0.8682 0.0167
-5.750 -0.1206 0.01771 0.01060 -0.1166 0.8572 0.0177
-5.500 -0.0919 0.01671 0.00943 -0.1170 0.8456 0.0190
-5.250 -0.0640 0.01583 0.00837 -0.1171 0.8337 0.0207
-5.000 -0.0363 0.01502 0.00737 -0.1173 0.8224 0.0227
-4.750 -0.0086 0.01444 0.00671 -0.1175 0.8116 0.0271
-4.500 0.0195 0.01391 0.00604 -0.1177 0.8015 0.0322
-4.250 0.0470 0.01349 0.00553 -0.1178 0.7910 0.0399
-4.000 0.0748 0.01304 0.00501 -0.1179 0.7813 0.0507
-3.750 0.1028 0.01262 0.00457 -0.1181 0.7724 0.0710
-3.500 0.1305 0.01226 0.00424 -0.1183 0.7631 0.1007
-3.250 0.1582 0.01190 0.00397 -0.1186 0.7547 0.1470
-3.000 0.1859 0.01148 0.00374 -0.1189 0.7466 0.2203
-2.750 0.2134 0.01102 0.00359 -0.1193 0.7386 0.3230
-2.500 0.2410 0.01078 0.00353 -0.1194 0.7313 0.4068
-2.250 0.2685 0.01068 0.00349 -0.1194 0.7237 0.4589
-2.000 0.2963 0.01064 0.00345 -0.1193 0.7170 0.5000
-1.750 0.3238 0.01061 0.00342 -0.1192 0.7098 0.5335
-1.500 0.3515 0.01062 0.00339 -0.1191 0.7034 0.5610
-1.250 0.3790 0.01062 0.00338 -0.1190 0.6967 0.5858
-1.000 0.4065 0.01062 0.00337 -0.1188 0.6904 0.6090
-0.750 0.4339 0.01064 0.00338 -0.1187 0.6845 0.6306
-0.500 0.4611 0.01065 0.00339 -0.1185 0.6782 0.6518
-0.250 0.4884 0.01068 0.00341 -0.1183 0.6728 0.6731
0.000 0.5152 0.01068 0.00345 -0.1180 0.6665 0.6940
0.250 0.5422 0.01071 0.00348 -0.1177 0.6610 0.7152
0.500 0.5685 0.01073 0.00354 -0.1173 0.6553 0.7359
0.750 0.5948 0.01076 0.00360 -0.1169 0.6495 0.7577
1.000 0.6207 0.01080 0.00365 -0.1164 0.6447 0.7804
1.250 0.6456 0.01081 0.00374 -0.1157 0.6385 0.8060
1.500 0.6699 0.01083 0.00381 -0.1148 0.6332 0.8354
1.750 0.6933 0.01084 0.00386 -0.1136 0.6280 0.8710
2.000 0.7169 0.01080 0.00390 -0.1125 0.6221 0.9205
2.250 0.7490 0.01083 0.00390 -0.1134 0.6170 1.0000
2.500 0.7772 0.01096 0.00405 -0.1137 0.6109 1.0000
2.750 0.8054 0.01111 0.00417 -0.1139 0.6051 1.0000
3.000 0.8334 0.01126 0.00430 -0.1140 0.5994 1.0000
3.250 0.8609 0.01140 0.00446 -0.1141 0.5926 1.0000
3.500 0.8885 0.01156 0.00461 -0.1141 0.5859 1.0000
3.750 0.9155 0.01170 0.00478 -0.1141 0.5777 1.0000
4.000 0.9425 0.01185 0.00494 -0.1140 0.5701 1.0000
4.250 0.9692 0.01200 0.00511 -0.1139 0.5616 1.0000
4.500 0.9956 0.01216 0.00532 -0.1137 0.5523 1.0000
4.750 1.0219 0.01232 0.00550 -0.1134 0.5431 1.0000
5.000 1.0478 0.01249 0.00570 -0.1131 0.5328 1.0000
5.250 1.0733 0.01267 0.00592 -0.1127 0.5210 1.0000
5.500 1.0985 0.01286 0.00617 -0.1123 0.5086 1.0000
5.750 1.1234 0.01306 0.00641 -0.1118 0.4954 1.0000
6.000 1.1477 0.01329 0.00667 -0.1112 0.4803 1.0000
6.250 1.1710 0.01355 0.00694 -0.1105 0.4621 1.0000
6.500 1.1938 0.01385 0.00725 -0.1096 0.4411 1.0000
6.750 1.2152 0.01422 0.00761 -0.1086 0.4170 1.0000
7.000 1.2349 0.01468 0.00801 -0.1073 0.3857 1.0000
7.250 1.2515 0.01532 0.00851 -0.1055 0.3460 1.0000
7.500 1.2644 0.01619 0.00916 -0.1033 0.2994 1.0000
7.750 1.2757 0.01719 0.00995 -0.1009 0.2565 1.0000
8.000 1.2861 0.01823 0.01081 -0.0984 0.2184 1.0000
8.250 1.2963 0.01925 0.01169 -0.0959 0.1860 1.0000
8.500 1.3044 0.02024 0.01261 -0.0931 0.1592 1.0000
8.750 1.3106 0.02136 0.01360 -0.0901 0.1324 1.0000
9.000 1.3149 0.02263 0.01472 -0.0871 0.1057 1.0000
9.250 1.3182 0.02403 0.01595 -0.0842 0.0806 1.0000
9.500 1.3221 0.02545 0.01726 -0.0815 0.0615 1.0000
9.750 1.3281 0.02681 0.01859 -0.0793 0.0485 1.0000
10.000 1.3343 0.02823 0.02002 -0.0772 0.0389 1.0000
10.250 1.3395 0.02980 0.02160 -0.0753 0.0306 1.0000
10.500 1.3433 0.03157 0.02338 -0.0734 0.0233 1.0000
10.750 1.3474 0.03342 0.02533 -0.0717 0.0182 1.0000
11.000 1.3496 0.03554 0.02752 -0.0700 0.0151 1.0000
11.250 1.3532 0.03762 0.02972 -0.0686 0.0131 1.0000
11.500 1.3545 0.04000 0.03218 -0.0674 0.0117 1.0000
11.750 1.3570 0.04235 0.03465 -0.0663 0.0107 1.0000
12.000 1.3606 0.04465 0.03708 -0.0655 0.0098 1.0000
12.250 1.3635 0.04709 0.03964 -0.0648 0.0090 1.0000
12.500 1.3644 0.04980 0.04247 -0.0642 0.0085 1.0000
12.750 1.3630 0.05289 0.04569 -0.0638 0.0082 1.0000
13.000 1.3597 0.05630 0.04923 -0.0634 0.0079 1.0000
13.250 1.3592 0.05948 0.05257 -0.0633 0.0077 1.0000
13.500 1.3581 0.06283 0.05608 -0.0633 0.0075 1.0000
13.750 1.3565 0.06635 0.05975 -0.0634 0.0073 1.0000
14.000 1.3545 0.07003 0.06359 -0.0637 0.0072 1.0000
14.250 1.3524 0.07383 0.06759 -0.0642 0.0070 1.0000
14.500 1.3501 0.07776 0.07167 -0.0648 0.0069 1.0000
14.750 1.3474 0.08185 0.07591 -0.0655 0.0067 1.0000
15.000 1.3445 0.08608 0.08030 -0.0664 0.0066 1.0000
15.250 1.3414 0.09043 0.08482 -0.0675 0.0065 1.0000
15.500 1.3377 0.09498 0.08954 -0.0688 0.0064 1.0000
15.750 1.3336 0.09971 0.09443 -0.0703 0.0063 1.0000
16.000 1.3289 0.10463 0.09952 -0.0720 0.0062 1.0000
16.250 1.3238 0.10976 0.10483 -0.0740 0.0062 1.0000
16.500 1.3178 0.11518 0.11043 -0.0763 0.0061 1.0000
16.750 1.3111 0.12087 0.11629 -0.0789 0.0061 1.0000
17.000 1.3036 0.12685 0.12246 -0.0819 0.0060 1.0000
17.250 1.2955 0.13314 0.12894 -0.0852 0.0060 1.0000
17.500 1.2867 0.13981 0.13579 -0.0890 0.0060 1.0000
17.750 1.2769 0.14691 0.14307 -0.0933 0.0060 1.0000
18.000 1.2661 0.15452 0.15087 -0.0981 0.0060 1.0000
18.250 1.2540 0.16274 0.15928 -0.1034 0.0060 1.0000
18.500 1.2404 0.17185 0.16858 -0.1094 0.0060 1.0000
18.750 1.2249 0.18206 0.17897 -0.1162 0.0061 1.0000
19.000 1.2040 0.19491 0.19201 -0.1247 0.0063 1.0000
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