EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 500,000 Max Cl/Cd: 68.98 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e485-il-500000-n5.txt Download as CSV file: xf-e485-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7866 0.11037 0.10762 -0.0155 1.0000 0.0036
-15.500 -0.8539 0.09161 0.08865 -0.0254 1.0000 0.0036
-15.250 -0.9094 0.07562 0.07237 -0.0346 1.0000 0.0033
-15.000 -0.9331 0.06643 0.06298 -0.0405 1.0000 0.0032
-14.750 -0.9555 0.05832 0.05467 -0.0458 1.0000 0.0032
-14.500 -0.9721 0.05220 0.04841 -0.0495 1.0000 0.0034
-14.250 -0.9845 0.04744 0.04345 -0.0515 1.0000 0.0032
-14.000 -0.9986 0.04310 0.03896 -0.0526 1.0000 0.0034
-13.750 -1.0068 0.03984 0.03553 -0.0527 1.0000 0.0033
-13.500 -1.0112 0.03723 0.03279 -0.0521 1.0000 0.0034
-13.250 -1.0140 0.03494 0.03036 -0.0510 1.0000 0.0034
-13.000 -1.0140 0.03303 0.02830 -0.0497 1.0000 0.0035
-12.750 -1.0111 0.03144 0.02661 -0.0481 1.0000 0.0036
-12.500 -1.0078 0.02996 0.02500 -0.0463 1.0000 0.0037
-12.250 -1.0058 0.02845 0.02336 -0.0440 1.0000 0.0037
-12.000 -1.0003 0.02725 0.02205 -0.0418 1.0000 0.0038
-11.750 -0.9948 0.02611 0.02079 -0.0393 1.0000 0.0038
-11.500 -0.9876 0.02515 0.01974 -0.0368 1.0000 0.0040
-11.250 -0.9813 0.02422 0.01869 -0.0339 1.0000 0.0041
-11.000 -0.9745 0.02335 0.01772 -0.0308 1.0000 0.0043
-10.750 -0.9639 0.02252 0.01680 -0.0284 1.0000 0.0045
-10.500 -0.9517 0.02176 0.01592 -0.0261 1.0000 0.0047
-10.250 -0.9396 0.02098 0.01504 -0.0237 1.0000 0.0047
-10.000 -0.9273 0.02021 0.01419 -0.0213 1.0000 0.0049
-9.750 -0.9141 0.01948 0.01340 -0.0191 1.0000 0.0051
-9.500 -0.8995 0.01889 0.01277 -0.0170 1.0000 0.0055
-9.250 -0.8851 0.01833 0.01215 -0.0148 1.0000 0.0057
-9.000 -0.8553 0.01762 0.01136 -0.0158 0.9960 0.0063
-8.750 -0.8255 0.01697 0.01062 -0.0167 0.9903 0.0067
-8.500 -0.7950 0.01630 0.00990 -0.0178 0.9845 0.0075
-8.250 -0.7653 0.01572 0.00928 -0.0187 0.9771 0.0083
-8.000 -0.7330 0.01522 0.00872 -0.0200 0.9699 0.0095
-7.750 -0.7030 0.01463 0.00811 -0.0209 0.9595 0.0110
-7.500 -0.6702 0.01419 0.00761 -0.0223 0.9494 0.0129
-7.250 -0.6378 0.01364 0.00704 -0.0236 0.9382 0.0151
-7.000 -0.6065 0.01323 0.00656 -0.0245 0.9255 0.0173
-6.750 -0.5793 0.01279 0.00610 -0.0246 0.9112 0.0203
-6.250 -0.5297 0.01216 0.00536 -0.0235 0.8839 0.0283
-6.000 -0.5058 0.01185 0.00503 -0.0228 0.8718 0.0345
-5.750 -0.4816 0.01158 0.00473 -0.0222 0.8608 0.0412
-5.500 -0.4571 0.01134 0.00445 -0.0215 0.8505 0.0486
-5.250 -0.4329 0.01106 0.00417 -0.0209 0.8402 0.0591
-5.000 -0.4085 0.01080 0.00392 -0.0203 0.8307 0.0721
-4.750 -0.3843 0.01052 0.00367 -0.0197 0.8215 0.0893
-4.500 -0.3598 0.01024 0.00344 -0.0191 0.8120 0.1103
-4.250 -0.3353 0.00997 0.00323 -0.0185 0.8032 0.1334
-4.000 -0.3110 0.00968 0.00301 -0.0179 0.7941 0.1642
-3.750 -0.2869 0.00935 0.00281 -0.0173 0.7852 0.2037
-3.500 -0.2629 0.00904 0.00262 -0.0167 0.7764 0.2468
-3.250 -0.2389 0.00870 0.00243 -0.0161 0.7669 0.2952
-3.000 -0.2151 0.00838 0.00226 -0.0155 0.7578 0.3488
-2.750 -0.1918 0.00802 0.00210 -0.0147 0.7481 0.4109
-2.500 -0.1683 0.00768 0.00195 -0.0139 0.7382 0.4726
-2.250 -0.1449 0.00737 0.00183 -0.0131 0.7286 0.5340
-2.000 -0.1214 0.00710 0.00174 -0.0122 0.7184 0.5958
-1.750 -0.0967 0.00692 0.00170 -0.0116 0.7081 0.6429
-1.500 -0.0711 0.00682 0.00166 -0.0110 0.6975 0.6789
-1.250 -0.0450 0.00678 0.00165 -0.0105 0.6864 0.7071
-1.000 -0.0186 0.00676 0.00164 -0.0101 0.6742 0.7302
-0.750 0.0081 0.00676 0.00164 -0.0097 0.6615 0.7488
-0.500 0.0350 0.00679 0.00164 -0.0094 0.6483 0.7639
-0.250 0.0618 0.00682 0.00165 -0.0090 0.6349 0.7775
0.000 0.0885 0.00687 0.00167 -0.0087 0.6207 0.7897
0.250 0.1153 0.00693 0.00170 -0.0084 0.6062 0.8000
0.500 0.1422 0.00701 0.00171 -0.0081 0.5907 0.8095
0.750 0.1689 0.00708 0.00175 -0.0078 0.5748 0.8173
1.000 0.1957 0.00718 0.00178 -0.0075 0.5580 0.8252
1.250 0.2221 0.00728 0.00184 -0.0072 0.5406 0.8320
1.500 0.2487 0.00739 0.00188 -0.0069 0.5231 0.8391
1.750 0.2751 0.00750 0.00195 -0.0065 0.5048 0.8447
2.000 0.3015 0.00763 0.00201 -0.0063 0.4860 0.8509
2.250 0.3277 0.00776 0.00208 -0.0059 0.4671 0.8560
2.500 0.3537 0.00790 0.00217 -0.0056 0.4481 0.8609
2.750 0.3798 0.00806 0.00225 -0.0053 0.4280 0.8663
3.000 0.4057 0.00822 0.00235 -0.0049 0.4082 0.8708
3.250 0.4313 0.00839 0.00247 -0.0045 0.3888 0.8752
3.500 0.4570 0.00856 0.00258 -0.0042 0.3694 0.8801
3.750 0.4826 0.00875 0.00271 -0.0038 0.3506 0.8846
4.000 0.5077 0.00894 0.00286 -0.0033 0.3322 0.8887
4.250 0.5330 0.00913 0.00300 -0.0029 0.3149 0.8933
4.500 0.5584 0.00933 0.00314 -0.0026 0.2975 0.8981
4.750 0.5832 0.00953 0.00332 -0.0020 0.2811 0.9019
5.000 0.6077 0.00975 0.00349 -0.0015 0.2646 0.9065
5.250 0.6325 0.00997 0.00367 -0.0010 0.2492 0.9114
5.500 0.6567 0.01020 0.00387 -0.0004 0.2341 0.9156
5.750 0.6807 0.01042 0.00408 0.0002 0.2202 0.9202
6.000 0.7047 0.01066 0.00429 0.0008 0.2064 0.9254
6.250 0.7286 0.01090 0.00451 0.0014 0.1935 0.9301
6.500 0.7521 0.01115 0.00475 0.0021 0.1817 0.9353
6.750 0.7753 0.01143 0.00501 0.0028 0.1690 0.9413
7.000 0.7991 0.01171 0.00528 0.0034 0.1574 0.9465
7.500 0.8479 0.01233 0.00586 0.0041 0.1338 0.9585
7.750 0.8745 0.01268 0.00621 0.0040 0.1219 0.9643
8.000 0.9008 0.01306 0.00657 0.0038 0.1106 0.9707
8.250 0.9299 0.01348 0.00697 0.0030 0.1001 0.9756
8.500 0.9580 0.01393 0.00740 0.0024 0.0906 0.9818
8.750 0.9876 0.01439 0.00786 0.0014 0.0809 0.9870
9.000 1.0165 0.01485 0.00833 0.0005 0.0728 0.9936
9.250 1.0418 0.01536 0.00882 0.0003 0.0651 1.0000
9.500 1.0573 0.01579 0.00924 0.0021 0.0586 1.0000
9.750 1.0740 0.01625 0.00971 0.0037 0.0532 1.0000
10.000 1.0910 0.01673 0.01021 0.0052 0.0483 1.0000
10.250 1.1071 0.01726 0.01075 0.0068 0.0435 1.0000
10.500 1.1217 0.01778 0.01129 0.0086 0.0390 1.0000
10.750 1.1341 0.01838 0.01189 0.0108 0.0350 1.0000
11.000 1.1475 0.01894 0.01249 0.0127 0.0318 1.0000
11.250 1.1586 0.01966 0.01321 0.0148 0.0280 1.0000
11.500 1.1712 0.02033 0.01392 0.0166 0.0253 1.0000
11.750 1.1823 0.02110 0.01473 0.0184 0.0230 1.0000
12.000 1.1923 0.02198 0.01565 0.0202 0.0206 1.0000
12.250 1.2030 0.02284 0.01658 0.0218 0.0187 1.0000
12.500 1.2114 0.02388 0.01766 0.0234 0.0167 1.0000
12.750 1.2199 0.02498 0.01881 0.0249 0.0151 1.0000
13.000 1.2282 0.02613 0.02003 0.0262 0.0137 1.0000
13.250 1.2343 0.02750 0.02146 0.0275 0.0123 1.0000
13.500 1.2406 0.02893 0.02295 0.0286 0.0112 1.0000
13.750 1.2461 0.03047 0.02458 0.0295 0.0102 1.0000
14.000 1.2500 0.03224 0.02642 0.0304 0.0093 1.0000
14.250 1.2523 0.03423 0.02849 0.0310 0.0085 1.0000
14.500 1.2551 0.03627 0.03063 0.0314 0.0079 1.0000
14.750 1.2561 0.03858 0.03304 0.0316 0.0073 1.0000
15.000 1.2550 0.04121 0.03577 0.0316 0.0067 1.0000
15.250 1.2519 0.04421 0.03886 0.0313 0.0063 1.0000
15.500 1.2482 0.04740 0.04217 0.0308 0.0060 1.0000
15.750 1.2444 0.05078 0.04567 0.0299 0.0057 1.0000
16.000 1.2398 0.05443 0.04944 0.0288 0.0054 1.0000
16.250 1.2321 0.05866 0.05380 0.0272 0.0052 1.0000
16.500 1.2229 0.06331 0.05857 0.0253 0.0050 1.0000
16.750 1.2131 0.06825 0.06364 0.0231 0.0049 1.0000
17.000 1.2007 0.07377 0.06929 0.0205 0.0047 1.0000
17.250 1.1874 0.07964 0.07529 0.0177 0.0046 1.0000
17.500 1.1719 0.08605 0.08184 0.0144 0.0046 1.0000
17.750 1.1532 0.09321 0.08914 0.0107 0.0045 1.0000
18.000 1.1342 0.10067 0.09674 0.0068 0.0044 1.0000
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Polar data table (+)
Polar graphs
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