EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 50,000 Max Cl/Cd: 27.43 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e485-il-50000.txt Download as CSV file: xf-e485-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 485 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3520 0.10127 0.09477 -0.0094 1.0000 0.3400
-9.500 -0.5603 0.08444 0.07782 -0.0323 1.0000 0.1476
-9.250 -0.6552 0.07620 0.06950 -0.0370 1.0000 0.1278
-9.000 -0.6536 0.07150 0.06476 -0.0363 1.0000 0.1258
-8.750 -0.6597 0.06714 0.06034 -0.0351 1.0000 0.1237
-8.500 -0.6716 0.06278 0.05584 -0.0332 1.0000 0.1211
-8.250 -0.7085 0.05841 0.05067 -0.0288 1.0000 0.1131
-8.000 -0.7095 0.05456 0.04654 -0.0261 1.0000 0.1129
-7.750 -0.7085 0.05088 0.04255 -0.0232 1.0000 0.1127
-7.500 -0.7053 0.04748 0.03875 -0.0202 1.0000 0.1128
-7.250 -0.6927 0.04438 0.03574 -0.0184 1.0000 0.1178
-7.000 -0.6854 0.04183 0.03288 -0.0154 1.0000 0.1228
-6.750 -0.6783 0.03914 0.02961 -0.0121 1.0000 0.1264
-6.500 -0.6637 0.03669 0.02716 -0.0101 1.0000 0.1345
-6.250 -0.6511 0.03447 0.02453 -0.0074 1.0000 0.1434
-6.000 -0.6353 0.03257 0.02237 -0.0052 1.0000 0.1556
-5.750 -0.6171 0.03059 0.02041 -0.0033 1.0000 0.1720
-5.500 -0.5985 0.02888 0.01884 -0.0016 1.0000 0.1944
-5.250 -0.5794 0.02723 0.01731 0.0002 1.0000 0.2245
-5.000 -0.5612 0.02562 0.01600 0.0022 1.0000 0.2676
-4.750 -0.5469 0.02392 0.01482 0.0048 1.0000 0.3359
-4.500 -0.5409 0.02202 0.01396 0.0090 1.0000 0.4537
-4.250 -0.5352 0.02165 0.01500 0.0170 1.0000 0.6507
-4.000 -0.5182 0.02354 0.01693 0.0246 1.0000 0.7600
-3.750 -0.4626 0.02653 0.01946 0.0269 1.0000 0.8338
-3.500 -0.2355 0.02934 0.02088 0.0003 1.0000 0.9166
-3.250 -0.1123 0.02806 0.01898 -0.0170 1.0000 0.9621
-3.000 -0.0054 0.02592 0.01637 -0.0336 1.0000 0.9983
-2.750 0.0000 0.02558 0.01599 -0.0322 1.0000 1.0000
-2.500 -0.0045 0.02552 0.01591 -0.0290 1.0000 1.0000
-2.250 -0.0118 0.02556 0.01591 -0.0254 1.0000 1.0000
-2.000 -0.0198 0.02565 0.01598 -0.0216 1.0000 1.0000
-1.750 -0.0273 0.02576 0.01605 -0.0179 1.0000 1.0000
-1.500 -0.0343 0.02587 0.01613 -0.0143 1.0000 1.0000
-1.250 -0.0405 0.02599 0.01621 -0.0109 1.0000 1.0000
-1.000 -0.0460 0.02613 0.01630 -0.0075 1.0000 1.0000
-0.750 -0.0508 0.02627 0.01640 -0.0042 1.0000 1.0000
-0.500 -0.0550 0.02642 0.01651 -0.0010 1.0000 1.0000
-0.250 -0.0586 0.02659 0.01664 0.0021 1.0000 1.0000
0.000 -0.0617 0.02677 0.01677 0.0052 1.0000 1.0000
0.250 -0.0140 0.02752 0.01744 -0.0009 0.9868 1.0000
0.500 0.0472 0.02839 0.01825 -0.0091 0.9694 1.0000
0.750 0.0963 0.02899 0.01882 -0.0148 0.9505 1.0000
1.000 0.1475 0.02958 0.01939 -0.0205 0.9317 1.0000
1.250 0.2042 0.03009 0.01992 -0.0268 0.9132 1.0000
1.500 0.2507 0.03050 0.02036 -0.0310 0.8935 1.0000
1.750 0.2953 0.03083 0.02075 -0.0346 0.8732 1.0000
2.000 0.3607 0.03090 0.02091 -0.0413 0.8540 1.0000
2.250 0.4122 0.03091 0.02103 -0.0452 0.8336 1.0000
2.500 0.4529 0.03087 0.02108 -0.0470 0.8123 1.0000
2.750 0.5058 0.03039 0.02073 -0.0500 0.7928 1.0000
3.000 0.5242 0.03063 0.02103 -0.0480 0.7701 1.0000
3.250 0.5608 0.03021 0.02071 -0.0480 0.7495 1.0000
3.500 0.5826 0.03021 0.02077 -0.0459 0.7276 1.0000
3.750 0.6080 0.02998 0.02064 -0.0441 0.7061 1.0000
4.000 0.6333 0.02970 0.02041 -0.0421 0.6851 1.0000
4.250 0.6516 0.02969 0.02046 -0.0394 0.6626 1.0000
4.500 0.6781 0.02925 0.02007 -0.0373 0.6415 1.0000
4.750 0.6938 0.02938 0.02026 -0.0343 0.6183 1.0000
5.000 0.7180 0.02908 0.01996 -0.0320 0.5964 1.0000
5.250 0.7351 0.02920 0.02011 -0.0292 0.5730 1.0000
5.500 0.7553 0.02922 0.02016 -0.0266 0.5503 1.0000
5.750 0.7752 0.02930 0.02024 -0.0241 0.5272 1.0000
6.000 0.7914 0.02969 0.02064 -0.0215 0.5043 1.0000
6.250 0.8131 0.02984 0.02073 -0.0193 0.4815 1.0000
6.500 0.8264 0.03054 0.02150 -0.0165 0.4591 1.0000
6.750 0.8474 0.03089 0.02178 -0.0144 0.4371 1.0000
7.000 0.8601 0.03177 0.02270 -0.0117 0.4157 1.0000
7.250 0.8774 0.03247 0.02339 -0.0094 0.3947 1.0000
7.500 0.8948 0.03329 0.02417 -0.0073 0.3743 1.0000
7.750 0.9062 0.03444 0.02545 -0.0046 0.3549 1.0000
8.000 0.9234 0.03541 0.02640 -0.0026 0.3356 1.0000
8.250 0.9428 0.03642 0.02734 -0.0008 0.3168 1.0000
8.500 0.9527 0.03795 0.02902 0.0017 0.3000 1.0000
8.750 0.9636 0.03947 0.03066 0.0040 0.2835 1.0000
9.000 0.9753 0.04119 0.03250 0.0062 0.2685 1.0000
9.250 0.9861 0.04290 0.03436 0.0084 0.2536 1.0000
9.500 0.9967 0.04477 0.03634 0.0105 0.2400 1.0000
9.750 1.0087 0.04675 0.03841 0.0123 0.2274 1.0000
10.000 1.0213 0.04855 0.04026 0.0141 0.2142 1.0000
10.250 1.0050 0.05206 0.04420 0.0176 0.2083 1.0000
10.500 1.0143 0.05448 0.04669 0.0193 0.1986 1.0000
10.750 0.9871 0.05872 0.05126 0.0226 0.1962 1.0000
11.000 0.9519 0.06343 0.05615 0.0256 0.1961 1.0000
11.250 0.9084 0.06954 0.06234 0.0267 0.1983 1.0000
11.500 0.8673 0.07727 0.07008 0.0250 0.2004 1.0000
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Polar data table (+)
Polar graphs
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