EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 500,000 Max Cl/Cd: 110.48 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e585-il-500000-n5.txt Download as CSV file: xf-e585-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.0462 0.10314 0.10036 -0.1010 0.8730 0.0060
-12.250 -0.0422 0.09987 0.09704 -0.1022 0.8632 0.0059
-12.000 -0.1573 0.11095 0.10839 -0.0901 0.9377 0.0060
-11.500 -0.1169 0.10037 0.09771 -0.1035 0.9205 0.0056
-11.250 -0.0986 0.09520 0.09245 -0.1100 0.9075 0.0053
-11.000 -0.0865 0.09016 0.08732 -0.1151 0.8905 0.0049
-10.750 -0.0829 0.08539 0.08246 -0.1182 0.8736 0.0049
-10.500 -0.0847 0.08067 0.07767 -0.1205 0.8580 0.0051
-10.250 -0.0884 0.07608 0.07303 -0.1224 0.8454 0.0053
-10.000 -0.0942 0.07130 0.06821 -0.1245 0.8344 0.0053
-9.750 -0.1022 0.06629 0.06317 -0.1268 0.8243 0.0050
-9.500 -0.1264 0.05753 0.05443 -0.1327 0.8140 0.0049
-9.250 -0.1778 0.04675 0.04347 -0.1378 0.8028 0.0046
-8.750 -0.2311 0.03680 0.03306 -0.1330 0.7869 0.0047
-8.500 -0.2567 0.02985 0.02556 -0.1293 0.7805 0.0048
-8.250 -0.2555 0.02640 0.02170 -0.1271 0.7757 0.0049
-8.000 -0.2476 0.02351 0.01838 -0.1253 0.7708 0.0050
-7.750 -0.2333 0.02137 0.01587 -0.1239 0.7665 0.0051
-7.500 -0.2147 0.01988 0.01407 -0.1230 0.7628 0.0052
-7.250 -0.1934 0.01876 0.01274 -0.1224 0.7591 0.0055
-7.000 -0.1712 0.01777 0.01153 -0.1218 0.7552 0.0057
-6.750 -0.1479 0.01697 0.01054 -0.1213 0.7515 0.0060
-6.500 -0.1238 0.01630 0.00969 -0.1209 0.7482 0.0062
-6.250 -0.0999 0.01552 0.00878 -0.1204 0.7450 0.0063
-6.000 -0.0766 0.01468 0.00784 -0.1199 0.7414 0.0064
-5.750 -0.0526 0.01403 0.00711 -0.1195 0.7378 0.0065
-5.500 -0.0283 0.01345 0.00645 -0.1191 0.7346 0.0066
-5.000 0.0220 0.01254 0.00543 -0.1187 0.7285 0.0071
-4.750 0.0477 0.01216 0.00500 -0.1185 0.7251 0.0074
-4.500 0.0738 0.01183 0.00461 -0.1184 0.7219 0.0079
-4.250 0.1003 0.01154 0.00425 -0.1183 0.7189 0.0084
-4.000 0.1268 0.01124 0.00389 -0.1183 0.7161 0.0097
-3.750 0.1536 0.01098 0.00361 -0.1182 0.7128 0.0118
-3.500 0.1805 0.01072 0.00337 -0.1183 0.7096 0.0181
-3.250 0.2073 0.01045 0.00316 -0.1184 0.7065 0.0367
-3.000 0.2341 0.01017 0.00299 -0.1185 0.7035 0.0666
-2.750 0.2610 0.00987 0.00285 -0.1187 0.7005 0.1160
-2.500 0.2877 0.00942 0.00271 -0.1190 0.6973 0.2031
-2.250 0.3145 0.00894 0.00257 -0.1195 0.6939 0.3131
-2.000 0.3416 0.00837 0.00241 -0.1200 0.6905 0.4529
-1.750 0.3680 0.00780 0.00242 -0.1203 0.6874 0.6386
-1.500 0.3957 0.00781 0.00250 -0.1202 0.6840 0.6877
-1.250 0.4236 0.00785 0.00255 -0.1203 0.6800 0.7087
-1.000 0.4517 0.00791 0.00256 -0.1204 0.6763 0.7227
-0.750 0.4798 0.00798 0.00259 -0.1205 0.6728 0.7346
-0.500 0.5075 0.00809 0.00268 -0.1204 0.6695 0.7506
-0.250 0.5344 0.00820 0.00281 -0.1202 0.6655 0.7645
0.000 0.5619 0.00827 0.00286 -0.1201 0.6617 0.7715
0.250 0.5898 0.00831 0.00286 -0.1203 0.6580 0.7741
0.500 0.6179 0.00836 0.00287 -0.1205 0.6542 0.7764
0.750 0.6459 0.00838 0.00288 -0.1207 0.6495 0.7786
1.000 0.6738 0.00843 0.00288 -0.1208 0.6446 0.7809
1.250 0.7018 0.00849 0.00289 -0.1211 0.6401 0.7831
1.500 0.7293 0.00851 0.00293 -0.1212 0.6348 0.7847
1.750 0.7564 0.00856 0.00296 -0.1212 0.6296 0.7863
2.000 0.7836 0.00862 0.00301 -0.1212 0.6248 0.7882
2.250 0.8107 0.00867 0.00307 -0.1212 0.6188 0.7902
2.500 0.8374 0.00874 0.00311 -0.1212 0.6127 0.7922
2.750 0.8643 0.00881 0.00318 -0.1212 0.6060 0.7942
3.000 0.8908 0.00889 0.00325 -0.1211 0.5991 0.7962
3.250 0.9174 0.00897 0.00332 -0.1211 0.5920 0.7984
3.500 0.9430 0.00906 0.00341 -0.1209 0.5841 0.8003
3.750 0.9686 0.00915 0.00351 -0.1206 0.5762 0.8021
4.000 0.9933 0.00927 0.00362 -0.1202 0.5676 0.8040
4.250 1.0184 0.00938 0.00374 -0.1199 0.5579 0.8060
4.500 1.0427 0.00952 0.00387 -0.1194 0.5479 0.8081
4.750 1.0661 0.00969 0.00402 -0.1188 0.5365 0.8104
5.000 1.0893 0.00987 0.00418 -0.1181 0.5239 0.8129
5.250 1.1114 0.01006 0.00436 -0.1172 0.5100 0.8152
5.500 1.1319 0.01028 0.00457 -0.1160 0.4947 0.8173
5.750 1.1512 0.01055 0.00480 -0.1146 0.4784 0.8196
6.000 1.1696 0.01083 0.00505 -0.1131 0.4617 0.8222
6.250 1.1858 0.01114 0.00532 -0.1111 0.4439 0.8250
6.500 1.2002 0.01149 0.00562 -0.1088 0.4259 0.8280
6.750 1.2138 0.01189 0.00597 -0.1064 0.4076 0.8310
7.000 1.2261 0.01234 0.00639 -0.1038 0.3888 0.8342
7.250 1.2384 0.01282 0.00683 -0.1013 0.3695 0.8377
7.500 1.2499 0.01338 0.00733 -0.0988 0.3492 0.8414
7.750 1.2599 0.01401 0.00789 -0.0961 0.3290 0.8450
8.000 1.2706 0.01460 0.00846 -0.0936 0.3122 0.8486
8.250 1.2810 0.01526 0.00909 -0.0911 0.2940 0.8529
8.500 1.2898 0.01603 0.00982 -0.0885 0.2742 0.8577
8.750 1.2985 0.01683 0.01058 -0.0860 0.2568 0.8628
9.000 1.3064 0.01770 0.01142 -0.0835 0.2396 0.8688
9.500 1.3217 0.01960 0.01327 -0.0788 0.2049 0.8826
9.750 1.3290 0.02061 0.01427 -0.0765 0.1889 0.8915
10.000 1.3350 0.02169 0.01534 -0.0741 0.1729 0.9039
10.250 1.3402 0.02281 0.01646 -0.0716 0.1574 0.9263
10.750 1.3559 0.02534 0.01894 -0.0685 0.1281 1.0000
11.000 1.3639 0.02669 0.02026 -0.0670 0.1154 1.0000
11.250 1.3716 0.02811 0.02165 -0.0656 0.1034 1.0000
11.500 1.3789 0.02959 0.02311 -0.0643 0.0919 1.0000
11.750 1.3853 0.03117 0.02466 -0.0629 0.0804 1.0000
12.000 1.3911 0.03285 0.02631 -0.0616 0.0695 1.0000
12.250 1.3968 0.03458 0.02802 -0.0604 0.0601 1.0000
12.500 1.4020 0.03639 0.02981 -0.0592 0.0511 1.0000
12.750 1.4060 0.03837 0.03176 -0.0580 0.0421 1.0000
13.000 1.4105 0.04036 0.03374 -0.0570 0.0353 1.0000
13.250 1.4133 0.04255 0.03593 -0.0560 0.0278 1.0000
13.500 1.4180 0.04464 0.03803 -0.0552 0.0235 1.0000
13.750 1.4207 0.04696 0.04036 -0.0544 0.0183 1.0000
14.000 1.4268 0.04902 0.04248 -0.0539 0.0162 1.0000
14.250 1.4295 0.05148 0.04496 -0.0533 0.0126 1.0000
14.500 1.4336 0.05384 0.04737 -0.0529 0.0109 1.0000
14.750 1.4381 0.05622 0.04982 -0.0526 0.0094 1.0000
15.000 1.4411 0.05883 0.05249 -0.0524 0.0080 1.0000
15.250 1.4453 0.06135 0.05511 -0.0522 0.0071 1.0000
15.500 1.4470 0.06423 0.05806 -0.0522 0.0059 1.0000
15.750 1.4500 0.06701 0.06093 -0.0523 0.0052 1.0000
16.000 1.4509 0.07011 0.06411 -0.0524 0.0045 1.0000
16.250 1.4526 0.07318 0.06727 -0.0527 0.0041 1.0000
16.500 1.4533 0.07646 0.07065 -0.0531 0.0035 1.0000
16.750 1.4526 0.07999 0.07427 -0.0536 0.0031 1.0000
17.000 1.4516 0.08361 0.07800 -0.0543 0.0027 1.0000
17.250 1.4509 0.08728 0.08177 -0.0551 0.0025 1.0000
17.500 1.4486 0.09123 0.08584 -0.0560 0.0022 1.0000
17.750 1.4440 0.09563 0.09033 -0.0572 0.0018 1.0000
18.000 1.4417 0.09973 0.09456 -0.0585 0.0018 1.0000
18.250 1.4382 0.10408 0.09904 -0.0599 0.0015 1.0000
18.500 1.4339 0.10863 0.10371 -0.0615 0.0014 1.0000
18.750 1.4286 0.11339 0.10859 -0.0633 0.0013 1.0000
19.000 1.4234 0.11822 0.11354 -0.0653 0.0012 1.0000
19.250 1.4163 0.12342 0.11885 -0.0675 0.0011 1.0000
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