EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.19 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e485-il-1000000.txt Download as CSV file: xf-e485-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8561 0.09468 0.09242 -0.0237 1.0000 0.0035
-15.500 -0.9079 0.07964 0.07718 -0.0322 1.0000 0.0034
-15.250 -0.9217 0.07228 0.06969 -0.0366 1.0000 0.0033
-15.000 -0.9327 0.06566 0.06296 -0.0409 1.0000 0.0033
-14.750 -0.9532 0.05777 0.05490 -0.0462 1.0000 0.0033
-14.500 -0.9887 0.04887 0.04575 -0.0514 1.0000 0.0033
-14.250 -0.9789 0.04707 0.04391 -0.0521 1.0000 0.0032
-14.000 -1.0051 0.04123 0.03782 -0.0537 1.0000 0.0033
-13.750 -1.0104 0.03829 0.03476 -0.0537 1.0000 0.0033
-13.500 -1.0231 0.03494 0.03122 -0.0528 1.0000 0.0033
-13.250 -1.0233 0.03295 0.02912 -0.0517 1.0000 0.0033
-13.000 -1.0314 0.03046 0.02645 -0.0496 1.0000 0.0033
-12.750 -1.0382 0.02824 0.02406 -0.0470 1.0000 0.0034
-12.500 -1.0367 0.02675 0.02244 -0.0446 1.0000 0.0034
-12.250 -1.0331 0.02549 0.02107 -0.0421 1.0000 0.0034
-12.000 -1.0329 0.02409 0.01954 -0.0389 1.0000 0.0035
-11.750 -1.0267 0.02319 0.01855 -0.0360 1.0000 0.0035
-11.500 -1.0237 0.02223 0.01750 -0.0324 1.0000 0.0036
-11.250 -1.0172 0.02140 0.01657 -0.0292 1.0000 0.0036
-11.000 -1.0065 0.02060 0.01570 -0.0266 1.0000 0.0038
-10.750 -0.9942 0.01988 0.01492 -0.0243 1.0000 0.0039
-10.500 -0.9810 0.01921 0.01418 -0.0220 1.0000 0.0041
-10.250 -0.9687 0.01847 0.01334 -0.0195 1.0000 0.0042
-10.000 -0.9552 0.01783 0.01263 -0.0172 1.0000 0.0043
-9.750 -0.9410 0.01726 0.01200 -0.0149 1.0000 0.0045
-9.500 -0.9247 0.01691 0.01160 -0.0128 1.0000 0.0048
-9.250 -0.9120 0.01596 0.01056 -0.0105 0.9995 0.0050
-9.000 -0.8800 0.01507 0.00961 -0.0120 0.9970 0.0056
-8.750 -0.8457 0.01455 0.00906 -0.0138 0.9945 0.0061
-8.500 -0.8129 0.01409 0.00855 -0.0151 0.9910 0.0068
-8.250 -0.7811 0.01336 0.00775 -0.0164 0.9867 0.0074
-8.000 -0.7466 0.01281 0.00720 -0.0182 0.9836 0.0087
-7.750 -0.7150 0.01240 0.00674 -0.0192 0.9770 0.0095
-7.500 -0.6820 0.01181 0.00615 -0.0207 0.9704 0.0114
-7.250 -0.6499 0.01145 0.00575 -0.0217 0.9599 0.0130
-7.000 -0.6183 0.01097 0.00526 -0.0228 0.9474 0.0156
-6.750 -0.5890 0.01066 0.00490 -0.0232 0.9319 0.0182
-6.500 -0.5637 0.01036 0.00457 -0.0227 0.9155 0.0218
-6.250 -0.5396 0.01009 0.00427 -0.0220 0.9005 0.0267
-6.000 -0.5153 0.00986 0.00400 -0.0213 0.8873 0.0324
-5.750 -0.4910 0.00962 0.00376 -0.0206 0.8754 0.0401
-5.500 -0.4666 0.00938 0.00352 -0.0200 0.8646 0.0502
-5.250 -0.4421 0.00913 0.00330 -0.0194 0.8541 0.0635
-5.000 -0.4175 0.00887 0.00307 -0.0188 0.8443 0.0796
-4.750 -0.3926 0.00864 0.00287 -0.0183 0.8352 0.0980
-4.500 -0.3679 0.00837 0.00268 -0.0177 0.8258 0.1220
-4.250 -0.3433 0.00808 0.00249 -0.0172 0.8171 0.1547
-4.000 -0.3193 0.00775 0.00230 -0.0166 0.8082 0.1992
-3.750 -0.2948 0.00743 0.00212 -0.0160 0.7993 0.2439
-3.500 -0.2708 0.00709 0.00196 -0.0154 0.7906 0.2971
-3.250 -0.2472 0.00669 0.00179 -0.0147 0.7814 0.3653
-3.000 -0.2235 0.00633 0.00164 -0.0141 0.7730 0.4339
-2.750 -0.1996 0.00599 0.00151 -0.0134 0.7640 0.5012
-2.500 -0.1751 0.00570 0.00140 -0.0128 0.7552 0.5612
-2.250 -0.1505 0.00547 0.00132 -0.0121 0.7464 0.6187
-2.000 -0.1247 0.00531 0.00127 -0.0116 0.7367 0.6625
-1.750 -0.0982 0.00522 0.00124 -0.0113 0.7271 0.6934
-1.500 -0.0716 0.00518 0.00122 -0.0109 0.7170 0.7207
-1.250 -0.0443 0.00515 0.00121 -0.0107 0.7063 0.7396
-1.000 -0.0169 0.00514 0.00120 -0.0105 0.6957 0.7558
-0.750 0.0106 0.00516 0.00119 -0.0103 0.6847 0.7693
-0.250 0.0658 0.00522 0.00120 -0.0100 0.6606 0.7927
0.000 0.0934 0.00525 0.00122 -0.0099 0.6480 0.8018
0.250 0.1210 0.00530 0.00123 -0.0098 0.6346 0.8107
0.500 0.1484 0.00536 0.00126 -0.0096 0.6205 0.8190
0.750 0.1759 0.00542 0.00129 -0.0094 0.6059 0.8268
1.000 0.2032 0.00550 0.00133 -0.0092 0.5906 0.8340
1.250 0.2306 0.00558 0.00136 -0.0091 0.5746 0.8405
1.500 0.2576 0.00567 0.00141 -0.0089 0.5575 0.8463
1.750 0.2848 0.00579 0.00146 -0.0087 0.5401 0.8525
2.000 0.3117 0.00588 0.00152 -0.0085 0.5221 0.8577
2.250 0.3386 0.00600 0.00159 -0.0083 0.5027 0.8631
2.500 0.3655 0.00614 0.00165 -0.0081 0.4830 0.8685
2.750 0.3918 0.00627 0.00173 -0.0078 0.4629 0.8730
3.000 0.4184 0.00641 0.00182 -0.0076 0.4426 0.8777
3.500 0.4710 0.00672 0.00200 -0.0070 0.4015 0.8866
3.750 0.4969 0.00689 0.00211 -0.0067 0.3802 0.8909
4.000 0.5230 0.00707 0.00223 -0.0064 0.3612 0.8954
4.250 0.5491 0.00724 0.00234 -0.0062 0.3417 0.8996
4.500 0.5744 0.00741 0.00247 -0.0057 0.3223 0.9036
5.000 0.6254 0.00782 0.00275 -0.0050 0.2856 0.9124
5.250 0.6504 0.00800 0.00290 -0.0045 0.2685 0.9165
5.500 0.6751 0.00820 0.00306 -0.0040 0.2520 0.9208
5.750 0.7001 0.00840 0.00323 -0.0035 0.2376 0.9255
6.000 0.7245 0.00861 0.00340 -0.0030 0.2219 0.9299
6.250 0.7483 0.00882 0.00358 -0.0023 0.2083 0.9346
6.500 0.7722 0.00904 0.00377 -0.0016 0.1948 0.9397
6.750 0.7957 0.00927 0.00397 -0.0009 0.1811 0.9447
7.000 0.8183 0.00950 0.00417 0.0000 0.1686 0.9503
7.250 0.8408 0.00976 0.00439 0.0009 0.1549 0.9565
7.500 0.8636 0.01002 0.00463 0.0017 0.1425 0.9626
8.000 0.9139 0.01062 0.00517 0.0022 0.1197 0.9750
8.250 0.9418 0.01096 0.00547 0.0018 0.1086 0.9806
8.500 0.9720 0.01132 0.00581 0.0008 0.0979 0.9847
8.750 1.0036 0.01174 0.00620 -0.0005 0.0867 0.9878
9.000 1.0343 0.01219 0.00660 -0.0017 0.0766 0.9914
9.250 1.0645 0.01268 0.00704 -0.0028 0.0668 0.9951
9.500 1.0956 0.01314 0.00748 -0.0042 0.0585 0.9988
9.750 1.1125 0.01349 0.00783 -0.0025 0.0530 1.0000
10.000 1.1272 0.01394 0.00824 -0.0005 0.0462 1.0000
10.250 1.1460 0.01432 0.00863 0.0008 0.0419 1.0000
10.500 1.1625 0.01488 0.00914 0.0023 0.0354 1.0000
10.750 1.1813 0.01529 0.00957 0.0036 0.0323 1.0000
11.000 1.1964 0.01590 0.01015 0.0053 0.0275 1.0000
11.250 1.2123 0.01631 0.01060 0.0070 0.0257 1.0000
11.500 1.2248 0.01686 0.01117 0.0092 0.0231 1.0000
11.750 1.2367 0.01746 0.01179 0.0115 0.0206 1.0000
12.000 1.2502 0.01801 0.01237 0.0133 0.0190 1.0000
12.250 1.2607 0.01873 0.01310 0.0154 0.0168 1.0000
12.500 1.2721 0.01943 0.01385 0.0173 0.0152 1.0000
12.750 1.2830 0.02019 0.01463 0.0191 0.0135 1.0000
13.000 1.2904 0.02119 0.01566 0.0212 0.0117 1.0000
13.250 1.3010 0.02203 0.01655 0.0227 0.0106 1.0000
13.500 1.3084 0.02313 0.01770 0.0244 0.0095 1.0000
13.750 1.3140 0.02440 0.01902 0.0260 0.0084 1.0000
14.000 1.3206 0.02568 0.02036 0.0274 0.0074 1.0000
14.250 1.3253 0.02715 0.02188 0.0286 0.0066 1.0000
14.500 1.3276 0.02890 0.02371 0.0299 0.0059 1.0000
14.750 1.3312 0.03064 0.02553 0.0308 0.0054 1.0000
15.000 1.3329 0.03262 0.02758 0.0315 0.0049 1.0000
15.250 1.3314 0.03501 0.03005 0.0321 0.0045 1.0000
15.500 1.3260 0.03793 0.03309 0.0324 0.0042 1.0000
15.750 1.3272 0.04032 0.03557 0.0324 0.0040 1.0000
16.000 1.3246 0.04323 0.03858 0.0321 0.0037 1.0000
16.250 1.3180 0.04676 0.04223 0.0314 0.0037 1.0000
16.500 1.3142 0.05012 0.04569 0.0305 0.0035 1.0000
16.750 1.3072 0.05409 0.04977 0.0293 0.0034 1.0000
17.000 1.2965 0.05875 0.05454 0.0275 0.0032 1.0000
17.250 1.2810 0.06434 0.06026 0.0252 0.0031 1.0000
17.500 1.2698 0.06953 0.06557 0.0228 0.0031 1.0000
17.750 1.2519 0.07596 0.07214 0.0197 0.0031 1.0000
18.000 1.2355 0.08240 0.07871 0.0165 0.0031 1.0000
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Polar data table (+)
Polar graphs
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