EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 500,000 Max Cl/Cd: 73.76 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e485-il-500000.txt Download as CSV file: xf-e485-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8545 0.04362 0.03982 -0.0530 1.0000 0.0069
-12.000 -0.8677 0.04045 0.03641 -0.0519 1.0000 0.0069
-11.750 -0.8793 0.03743 0.03321 -0.0500 1.0000 0.0069
-11.250 -0.8976 0.03250 0.02777 -0.0440 1.0000 0.0070
-11.000 -0.9096 0.02956 0.02456 -0.0398 1.0000 0.0072
-10.750 -0.9109 0.02792 0.02279 -0.0361 1.0000 0.0074
-10.500 -0.9050 0.02703 0.02185 -0.0332 1.0000 0.0077
-10.250 -0.8978 0.02564 0.02031 -0.0304 1.0000 0.0078
-10.000 -0.8879 0.02457 0.01913 -0.0278 1.0000 0.0080
-9.750 -0.8769 0.02360 0.01805 -0.0254 1.0000 0.0083
-9.500 -0.8647 0.02270 0.01704 -0.0229 1.0000 0.0088
-9.250 -0.8530 0.02169 0.01591 -0.0204 1.0000 0.0091
-9.000 -0.8406 0.02082 0.01491 -0.0178 1.0000 0.0095
-8.750 -0.8304 0.01985 0.01383 -0.0149 1.0000 0.0098
-8.500 -0.8252 0.01875 0.01267 -0.0113 1.0000 0.0105
-8.250 -0.8161 0.01816 0.01205 -0.0082 0.9997 0.0108
-8.000 -0.7808 0.01742 0.01126 -0.0103 0.9965 0.0121
-7.750 -0.7466 0.01650 0.01024 -0.0121 0.9928 0.0135
-7.500 -0.7126 0.01587 0.00963 -0.0140 0.9882 0.0157
-7.250 -0.6777 0.01504 0.00871 -0.0159 0.9843 0.0181
-7.000 -0.6440 0.01446 0.00815 -0.0175 0.9791 0.0214
-6.750 -0.6110 0.01366 0.00732 -0.0190 0.9735 0.0255
-6.500 -0.5739 0.01317 0.00680 -0.0211 0.9699 0.0298
-6.250 -0.5445 0.01251 0.00615 -0.0218 0.9605 0.0369
-6.000 -0.5115 0.01196 0.00562 -0.0231 0.9532 0.0467
-5.750 -0.4808 0.01147 0.00515 -0.0238 0.9437 0.0593
-5.500 -0.4528 0.01100 0.00473 -0.0240 0.9327 0.0756
-5.250 -0.4265 0.01058 0.00437 -0.0238 0.9215 0.0973
-5.000 -0.4019 0.01019 0.00406 -0.0233 0.9102 0.1266
-4.750 -0.3792 0.00977 0.00378 -0.0224 0.8983 0.1653
-4.500 -0.3570 0.00936 0.00353 -0.0214 0.8869 0.2134
-4.250 -0.3349 0.00892 0.00329 -0.0204 0.8764 0.2697
-4.000 -0.3135 0.00846 0.00305 -0.0193 0.8667 0.3388
-3.750 -0.2930 0.00795 0.00284 -0.0180 0.8561 0.4197
-3.500 -0.2722 0.00750 0.00266 -0.0167 0.8465 0.4990
-3.250 -0.2508 0.00713 0.00252 -0.0154 0.8375 0.5735
-3.000 -0.2279 0.00687 0.00244 -0.0143 0.8276 0.6326
-2.750 -0.2036 0.00673 0.00240 -0.0134 0.8188 0.6793
-2.500 -0.1783 0.00666 0.00238 -0.0126 0.8094 0.7127
-2.250 -0.1522 0.00664 0.00236 -0.0120 0.8002 0.7377
-2.000 -0.1258 0.00665 0.00235 -0.0114 0.7916 0.7590
-1.750 -0.0993 0.00666 0.00235 -0.0110 0.7817 0.7759
-1.500 -0.0725 0.00669 0.00235 -0.0105 0.7724 0.7902
-1.250 -0.0458 0.00674 0.00236 -0.0100 0.7630 0.8025
-1.000 -0.0190 0.00677 0.00238 -0.0095 0.7524 0.8139
-0.750 0.0076 0.00683 0.00238 -0.0091 0.7423 0.8248
-0.250 0.0610 0.00694 0.00244 -0.0081 0.7206 0.8422
0.000 0.0875 0.00701 0.00247 -0.0076 0.7091 0.8509
0.250 0.1140 0.00708 0.00251 -0.0071 0.6977 0.8581
0.500 0.1403 0.00715 0.00253 -0.0066 0.6856 0.8654
0.750 0.1666 0.00721 0.00255 -0.0060 0.6730 0.8717
1.000 0.1928 0.00728 0.00260 -0.0055 0.6595 0.8778
1.250 0.2188 0.00734 0.00261 -0.0050 0.6454 0.8844
1.500 0.2447 0.00741 0.00266 -0.0044 0.6309 0.8894
1.750 0.2703 0.00749 0.00269 -0.0038 0.6158 0.8956
2.000 0.2958 0.00756 0.00272 -0.0032 0.5999 0.9007
2.250 0.3211 0.00766 0.00277 -0.0025 0.5835 0.9056
2.500 0.3462 0.00774 0.00281 -0.0019 0.5660 0.9114
2.750 0.3713 0.00783 0.00286 -0.0012 0.5472 0.9159
3.000 0.3960 0.00795 0.00292 -0.0005 0.5281 0.9207
3.250 0.4200 0.00808 0.00299 0.0003 0.5086 0.9264
3.500 0.4447 0.00819 0.00305 0.0010 0.4879 0.9307
3.750 0.4691 0.00834 0.00314 0.0017 0.4671 0.9355
4.000 0.4923 0.00849 0.00323 0.0026 0.4461 0.9414
4.250 0.5175 0.00865 0.00333 0.0031 0.4243 0.9455
4.500 0.5429 0.00884 0.00346 0.0036 0.4028 0.9502
4.750 0.5655 0.00901 0.00357 0.0045 0.3819 0.9564
5.000 0.5943 0.00925 0.00374 0.0042 0.3597 0.9597
5.250 0.6234 0.00949 0.00392 0.0037 0.3377 0.9635
5.500 0.6493 0.00975 0.00410 0.0038 0.3173 0.9687
5.750 0.6803 0.01000 0.00432 0.0029 0.2966 0.9717
6.000 0.7135 0.01032 0.00456 0.0014 0.2756 0.9740
6.250 0.7463 0.01063 0.00481 -0.0001 0.2566 0.9766
6.500 0.7783 0.01094 0.00508 -0.0013 0.2381 0.9795
6.750 0.8083 0.01126 0.00536 -0.0022 0.2206 0.9832
7.000 0.8426 0.01163 0.00566 -0.0041 0.2029 0.9848
7.250 0.8761 0.01200 0.00599 -0.0057 0.1860 0.9870
7.500 0.9085 0.01237 0.00633 -0.0072 0.1697 0.9898
7.750 0.9392 0.01276 0.00668 -0.0083 0.1541 0.9931
8.000 0.9714 0.01317 0.00706 -0.0098 0.1393 0.9957
8.250 1.0037 0.01362 0.00747 -0.0114 0.1255 0.9985
8.500 1.0256 0.01403 0.00787 -0.0109 0.1141 1.0000
8.750 1.0310 0.01436 0.00817 -0.0070 0.1060 1.0000
9.000 1.0380 0.01463 0.00847 -0.0033 0.0990 1.0000
9.250 1.0472 0.01506 0.00886 -0.0002 0.0907 1.0000
9.500 1.0627 0.01546 0.00926 0.0017 0.0827 1.0000
9.750 1.0789 0.01595 0.00975 0.0034 0.0752 1.0000
10.000 1.0937 0.01656 0.01033 0.0052 0.0676 1.0000
10.250 1.1109 0.01702 0.01084 0.0066 0.0616 1.0000
10.500 1.1222 0.01773 0.01151 0.0090 0.0550 1.0000
10.750 1.1372 0.01820 0.01204 0.0108 0.0504 1.0000
11.000 1.1447 0.01907 0.01288 0.0135 0.0448 1.0000
11.250 1.1601 0.01956 0.01345 0.0151 0.0412 1.0000
11.500 1.1697 0.02040 0.01427 0.0172 0.0369 1.0000
11.750 1.1795 0.02125 0.01519 0.0192 0.0340 1.0000
12.000 1.1913 0.02203 0.01602 0.0208 0.0310 1.0000
12.250 1.1953 0.02333 0.01733 0.0229 0.0278 1.0000
12.500 1.2067 0.02421 0.01830 0.0243 0.0257 1.0000
12.750 1.2157 0.02529 0.01942 0.0256 0.0234 1.0000
13.000 1.2153 0.02708 0.02126 0.0274 0.0211 1.0000
13.250 1.2251 0.02823 0.02250 0.0284 0.0195 1.0000
13.500 1.2319 0.02966 0.02399 0.0294 0.0178 1.0000
13.750 1.2295 0.03193 0.02631 0.0305 0.0163 1.0000
14.000 1.2314 0.03396 0.02845 0.0312 0.0150 1.0000
14.250 1.2356 0.03586 0.03045 0.0317 0.0139 1.0000
14.500 1.2347 0.03836 0.03303 0.0319 0.0128 1.0000
14.750 1.2234 0.04209 0.03686 0.0318 0.0119 1.0000
15.000 1.2214 0.04504 0.03994 0.0314 0.0112 1.0000
15.250 1.2182 0.04826 0.04328 0.0308 0.0105 1.0000
15.500 1.2132 0.05186 0.04699 0.0298 0.0100 1.0000
15.750 1.2059 0.05595 0.05119 0.0284 0.0095 1.0000
16.000 1.1951 0.06072 0.05606 0.0265 0.0092 1.0000
16.250 1.1762 0.06694 0.06241 0.0238 0.0088 1.0000
16.500 1.1573 0.07339 0.06898 0.0208 0.0086 1.0000
16.750 1.1461 0.07891 0.07464 0.0182 0.0085 1.0000
17.000 1.1358 0.08449 0.08035 0.0155 0.0083 1.0000
17.250 1.1248 0.09027 0.08625 0.0126 0.0081 1.0000
17.500 1.1104 0.09676 0.09286 0.0093 0.0081 1.0000
17.750 1.0963 0.10336 0.09959 0.0058 0.0079 1.0000
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