EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 50,000 Max Cl/Cd: 4.91 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e655-il-50000.txt Download as CSV file: xf-e655-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 655 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4659 0.11774 0.11272 -0.0042 1.0000 0.3406
-7.000 -0.6954 0.08635 0.08103 -0.0319 1.0000 0.1359
-6.750 -0.6929 0.08210 0.07670 -0.0309 1.0000 0.1320
-6.500 -0.7148 0.07265 0.06632 -0.0334 1.0000 0.1195
-6.250 -0.7080 0.06829 0.06178 -0.0330 1.0000 0.1184
-6.000 -0.6995 0.06393 0.05711 -0.0328 1.0000 0.1171
-5.750 -0.6885 0.05950 0.05214 -0.0330 1.0000 0.1171
-5.500 -0.6735 0.05564 0.04757 -0.0332 1.0000 0.1189
-5.250 -0.6567 0.05249 0.04413 -0.0331 1.0000 0.1220
-5.000 -0.6385 0.05030 0.04178 -0.0326 1.0000 0.1273
-4.750 -0.6171 0.04792 0.03871 -0.0326 1.0000 0.1339
-4.500 -0.5976 0.04597 0.03674 -0.0321 1.0000 0.1414
-4.250 -0.5757 0.04427 0.03462 -0.0317 1.0000 0.1520
-4.000 -0.5546 0.04301 0.03319 -0.0312 1.0000 0.1653
-3.750 -0.5335 0.04183 0.03190 -0.0306 1.0000 0.1821
-3.500 -0.5137 0.04076 0.03103 -0.0297 1.0000 0.2032
-3.250 -0.4930 0.03989 0.03026 -0.0288 1.0000 0.2338
-3.000 -0.4732 0.03904 0.02973 -0.0278 1.0000 0.2774
-2.750 -0.4536 0.03795 0.02924 -0.0269 1.0000 0.3541
-2.500 -0.4403 0.03675 0.02975 -0.0234 1.0000 0.5329
-2.250 -0.4461 0.03782 0.03150 -0.0135 1.0000 0.6896
-2.000 -0.4509 0.03897 0.03262 -0.0045 1.0000 0.7667
-1.750 -0.4560 0.03973 0.03328 0.0043 1.0000 0.8226
-1.500 -0.4598 0.04016 0.03360 0.0126 1.0000 0.8722
-1.250 -0.4381 0.04122 0.03442 0.0162 1.0000 0.9311
-1.000 -0.2184 0.04875 0.04083 -0.0201 1.0000 1.0000
-0.750 -0.2191 0.04814 0.04007 -0.0179 1.0000 1.0000
-0.500 -0.2191 0.04760 0.03939 -0.0157 1.0000 1.0000
-0.250 -0.2185 0.04710 0.03875 -0.0135 1.0000 1.0000
0.000 -0.2176 0.04664 0.03816 -0.0113 1.0000 1.0000
0.250 -0.2160 0.04621 0.03761 -0.0091 1.0000 1.0000
0.500 -0.2137 0.04584 0.03711 -0.0071 1.0000 1.0000
0.750 -0.2104 0.04553 0.03668 -0.0052 1.0000 1.0000
1.000 -0.2043 0.04541 0.03643 -0.0038 1.0000 1.0000
1.250 -0.1942 0.04556 0.03646 -0.0031 1.0000 1.0000
1.500 -0.1749 0.04640 0.03714 -0.0042 0.9975 1.0000
1.750 -0.1429 0.04827 0.03884 -0.0077 0.9893 1.0000
2.000 -0.1096 0.05047 0.04084 -0.0113 0.9813 1.0000
2.250 -0.0750 0.05268 0.04290 -0.0152 0.9710 1.0000
2.500 -0.0472 0.05410 0.04419 -0.0177 0.9591 1.0000
2.750 -0.0210 0.05557 0.04555 -0.0199 0.9474 1.0000
3.000 0.0067 0.05738 0.04725 -0.0223 0.9368 1.0000
3.250 0.0446 0.06031 0.05005 -0.0265 0.9267 1.0000
3.500 0.0654 0.06123 0.05091 -0.0276 0.9130 1.0000
3.750 0.0871 0.06263 0.05225 -0.0289 0.9005 1.0000
4.000 0.1200 0.06544 0.05496 -0.0322 0.8919 1.0000
4.250 0.1466 0.06716 0.05663 -0.0341 0.8782 1.0000
4.500 0.1632 0.06824 0.05768 -0.0346 0.8650 1.0000
4.750 0.1849 0.07009 0.05949 -0.0359 0.8541 1.0000
5.000 0.2232 0.07346 0.06280 -0.0398 0.8435 1.0000
5.250 0.2349 0.07415 0.06350 -0.0395 0.8297 1.0000
5.500 0.2512 0.07573 0.06507 -0.0400 0.8177 1.0000
5.750 0.2891 0.07944 0.06875 -0.0437 0.8089 1.0000
6.000 0.3026 0.08042 0.06973 -0.0437 0.7946 1.0000
6.250 0.3138 0.08177 0.07111 -0.0437 0.7822 1.0000
6.500 0.3388 0.08455 0.07389 -0.0456 0.7730 1.0000
6.750 0.3663 0.08705 0.07641 -0.0475 0.7598 1.0000
7.000 0.3729 0.08818 0.07757 -0.0470 0.7469 1.0000
7.250 0.3896 0.09048 0.07991 -0.0478 0.7367 1.0000
7.500 0.4268 0.09412 0.08358 -0.0509 0.7253 1.0000
7.750 0.4285 0.09496 0.08447 -0.0499 0.7120 1.0000
8.000 0.4394 0.09709 0.08664 -0.0503 0.7016 1.0000
8.250 0.4745 0.10085 0.09046 -0.0530 0.6912 1.0000
8.500 0.4809 0.10213 0.09180 -0.0527 0.6777 1.0000
8.750 0.4862 0.10415 0.09388 -0.0527 0.6674 1.0000
9.000 0.5134 0.10753 0.09731 -0.0547 0.6575 1.0000
9.250 0.5323 0.10985 0.09972 -0.0556 0.6438 1.0000
9.500 0.5301 0.11161 0.10154 -0.0552 0.6339 1.0000
9.750 0.5503 0.11475 0.10475 -0.0566 0.6243 1.0000
10.000 0.5794 0.11795 0.10803 -0.0582 0.6108 1.0000
10.250 0.5726 0.11943 0.10958 -0.0577 0.6005 1.0000
10.500 0.5864 0.12254 0.11279 -0.0588 0.5924 1.0000
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Polar data table (+)
Polar graphs
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