EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.28 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e585-il-1000000-n5.txt Download as CSV file: xf-e585-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 585 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0928 0.09582 0.09327 -0.1158 0.8381 0.0028
-11.500 -0.0934 0.09183 0.08924 -0.1171 0.8260 0.0029
-11.000 -0.4270 0.03028 0.02693 -0.1379 0.7944 0.0027
-10.750 -0.4211 0.02957 0.02617 -0.1361 0.7878 0.0028
-10.500 -0.3945 0.03051 0.02721 -0.1358 0.7821 0.0029
-10.250 -0.3901 0.02975 0.02635 -0.1336 0.7760 0.0030
-10.000 -0.3955 0.02711 0.02345 -0.1311 0.7699 0.0030
-9.750 -0.3981 0.02433 0.02032 -0.1284 0.7643 0.0030
-9.500 -0.3894 0.02247 0.01820 -0.1268 0.7600 0.0031
-9.250 -0.3761 0.02094 0.01645 -0.1255 0.7557 0.0032
-9.000 -0.3596 0.01972 0.01503 -0.1244 0.7513 0.0032
-8.500 -0.3208 0.01774 0.01271 -0.1229 0.7440 0.0034
-8.250 -0.2993 0.01691 0.01173 -0.1223 0.7404 0.0035
-8.000 -0.2779 0.01601 0.01067 -0.1217 0.7367 0.0036
-7.750 -0.2558 0.01520 0.00970 -0.1211 0.7331 0.0036
-7.500 -0.2324 0.01453 0.00892 -0.1207 0.7301 0.0037
-7.250 -0.2082 0.01394 0.00822 -0.1204 0.7270 0.0038
-7.000 -0.1840 0.01335 0.00753 -0.1200 0.7236 0.0038
-6.750 -0.1594 0.01285 0.00693 -0.1197 0.7203 0.0039
-6.500 -0.1346 0.01239 0.00639 -0.1194 0.7172 0.0039
-6.250 -0.1090 0.01196 0.00590 -0.1193 0.7145 0.0040
-6.000 -0.0830 0.01160 0.00548 -0.1192 0.7115 0.0041
-5.750 -0.0565 0.01135 0.00519 -0.1192 0.7083 0.0042
-5.500 -0.0314 0.01084 0.00460 -0.1189 0.7052 0.0044
-5.250 -0.0055 0.01048 0.00420 -0.1188 0.7024 0.0046
-5.000 0.0213 0.01020 0.00388 -0.1188 0.6998 0.0048
-4.750 0.0483 0.00993 0.00358 -0.1189 0.6968 0.0050
-4.500 0.0755 0.00969 0.00331 -0.1189 0.6937 0.0052
-4.250 0.1027 0.00948 0.00306 -0.1190 0.6908 0.0055
-4.000 0.1300 0.00930 0.00283 -0.1190 0.6879 0.0059
-3.750 0.1575 0.00912 0.00262 -0.1192 0.6851 0.0067
-3.500 0.1854 0.00893 0.00243 -0.1193 0.6822 0.0089
-3.250 0.2132 0.00876 0.00227 -0.1195 0.6791 0.0145
-3.000 0.2408 0.00858 0.00214 -0.1197 0.6758 0.0262
-2.750 0.2683 0.00842 0.00202 -0.1199 0.6726 0.0432
-2.500 0.2960 0.00819 0.00191 -0.1202 0.6694 0.0791
-2.250 0.3237 0.00786 0.00181 -0.1206 0.6658 0.1466
-2.000 0.3514 0.00754 0.00172 -0.1210 0.6620 0.2237
-1.750 0.3792 0.00726 0.00164 -0.1214 0.6583 0.3022
-1.500 0.4073 0.00696 0.00156 -0.1219 0.6551 0.3911
-1.250 0.4359 0.00631 0.00146 -0.1228 0.6517 0.5738
-1.000 0.4644 0.00613 0.00150 -0.1232 0.6479 0.6591
-0.750 0.4927 0.00614 0.00153 -0.1234 0.6441 0.6853
-0.500 0.5210 0.00618 0.00155 -0.1236 0.6405 0.7000
-0.250 0.5496 0.00620 0.00159 -0.1238 0.6365 0.7126
0.000 0.5778 0.00625 0.00163 -0.1240 0.6314 0.7268
0.500 0.6337 0.00640 0.00175 -0.1242 0.6214 0.7495
0.750 0.6620 0.00646 0.00177 -0.1244 0.6160 0.7523
1.000 0.6895 0.00651 0.00180 -0.1245 0.6109 0.7541
1.250 0.7177 0.00655 0.00183 -0.1247 0.6054 0.7559
1.500 0.7451 0.00662 0.00187 -0.1248 0.5990 0.7577
1.750 0.7727 0.00668 0.00192 -0.1249 0.5925 0.7595
2.000 0.7999 0.00676 0.00197 -0.1250 0.5849 0.7612
2.250 0.8272 0.00684 0.00203 -0.1251 0.5778 0.7632
2.500 0.8541 0.00694 0.00209 -0.1251 0.5696 0.7651
2.750 0.8810 0.00703 0.00216 -0.1251 0.5617 0.7668
3.000 0.9071 0.00715 0.00224 -0.1249 0.5526 0.7684
3.250 0.9336 0.00725 0.00233 -0.1249 0.5430 0.7700
3.500 0.9592 0.00737 0.00243 -0.1246 0.5328 0.7716
3.750 0.9842 0.00752 0.00256 -0.1243 0.5214 0.7735
4.000 1.0091 0.00769 0.00268 -0.1239 0.5084 0.7755
4.250 1.0332 0.00787 0.00282 -0.1234 0.4938 0.7775
4.750 1.0793 0.00833 0.00317 -0.1221 0.4606 0.7812
5.000 1.1014 0.00859 0.00336 -0.1212 0.4425 0.7830
5.250 1.1226 0.00887 0.00357 -0.1202 0.4244 0.7848
5.500 1.1430 0.00916 0.00382 -0.1190 0.4060 0.7869
5.750 1.1624 0.00948 0.00407 -0.1177 0.3879 0.7891
6.000 1.1803 0.00981 0.00433 -0.1160 0.3681 0.7914
6.250 1.1960 0.01015 0.00461 -0.1140 0.3489 0.7938
6.500 1.2106 0.01054 0.00493 -0.1117 0.3296 0.7961
6.750 1.2255 0.01096 0.00527 -0.1096 0.3110 0.7983
7.000 1.2397 0.01140 0.00564 -0.1073 0.2917 0.8006
7.250 1.2547 0.01181 0.00603 -0.1053 0.2758 0.8031
7.500 1.2678 0.01231 0.00646 -0.1030 0.2577 0.8060
7.750 1.2798 0.01287 0.00695 -0.1006 0.2398 0.8091
8.000 1.2924 0.01342 0.00745 -0.0983 0.2235 0.8121
8.250 1.3044 0.01402 0.00799 -0.0961 0.2072 0.8147
8.500 1.3150 0.01468 0.00861 -0.0936 0.1898 0.8177
8.750 1.3254 0.01539 0.00927 -0.0913 0.1741 0.8210
9.000 1.3351 0.01617 0.01000 -0.0889 0.1582 0.8245
9.250 1.3439 0.01704 0.01081 -0.0866 0.1425 0.8281
9.500 1.3501 0.01808 0.01178 -0.0840 0.1235 0.8320
9.750 1.3588 0.01904 0.01270 -0.0818 0.1098 0.8365
10.000 1.3624 0.02034 0.01391 -0.0792 0.0899 0.8415
10.250 1.3690 0.02153 0.01504 -0.0770 0.0759 0.8462
10.500 1.3747 0.02280 0.01627 -0.0748 0.0615 0.8516
10.750 1.3827 0.02399 0.01745 -0.0730 0.0522 0.8575
11.000 1.3892 0.02530 0.01874 -0.0712 0.0422 0.8639
11.250 1.3968 0.02658 0.02003 -0.0695 0.0352 0.8720
11.500 1.4035 0.02792 0.02139 -0.0678 0.0286 0.8822
11.750 1.4107 0.02922 0.02273 -0.0661 0.0238 0.8971
12.000 1.4166 0.03037 0.02401 -0.0641 0.0200 0.9368
12.500 1.4334 0.03339 0.02707 -0.0622 0.0128 1.0000
12.750 1.4415 0.03494 0.02864 -0.0611 0.0105 1.0000
13.000 1.4502 0.03646 0.03021 -0.0602 0.0090 1.0000
13.250 1.4577 0.03813 0.03191 -0.0593 0.0072 1.0000
13.500 1.4652 0.03985 0.03366 -0.0585 0.0060 1.0000
13.750 1.4719 0.04168 0.03554 -0.0577 0.0046 1.0000
14.000 1.4798 0.04343 0.03734 -0.0570 0.0041 1.0000
14.250 1.4851 0.04549 0.03943 -0.0563 0.0031 1.0000
14.500 1.4921 0.04741 0.04141 -0.0558 0.0027 1.0000
14.750 1.4982 0.04947 0.04354 -0.0553 0.0022 1.0000
15.000 1.5020 0.05183 0.04596 -0.0548 0.0015 1.0000
15.250 1.5087 0.05392 0.04812 -0.0545 0.0015 1.0000
15.500 1.5111 0.05654 0.05080 -0.0541 0.0010 1.0000
15.750 1.5152 0.05903 0.05336 -0.0540 0.0008 1.0000
16.000 1.5174 0.06180 0.05620 -0.0538 0.0006 1.0000
16.250 1.5214 0.06440 0.05888 -0.0538 0.0006 1.0000
16.500 1.5220 0.06748 0.06205 -0.0539 0.0004 1.0000
16.750 1.5236 0.07050 0.06515 -0.0542 0.0003 1.0000
17.000 1.5250 0.07362 0.06836 -0.0545 0.0003 1.0000
17.250 1.5256 0.07690 0.07173 -0.0549 0.0003 1.0000
17.500 1.5253 0.08038 0.07530 -0.0555 0.0002 1.0000
17.750 1.5222 0.08432 0.07934 -0.0563 0.0002 1.0000
18.000 1.5226 0.08781 0.08292 -0.0571 0.0002 1.0000
18.250 1.5182 0.09212 0.08733 -0.0581 0.0002 1.0000
18.500 1.5150 0.09630 0.09161 -0.0593 0.0001 1.0000
18.750 1.5092 0.10095 0.09639 -0.0608 0.0001 1.0000
19.000 1.5052 0.10538 0.10092 -0.0623 0.0001 1.0000
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Polar data table (+)
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