EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.09 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e585-il-1000000.txt Download as CSV file: xf-e585-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0604 0.07972 0.07764 -0.1257 0.8984 0.0086
-10.250 -0.0603 0.07484 0.07263 -0.1283 0.8732 0.0086
-7.500 -0.2065 0.01910 0.01429 -0.1254 0.7698 0.0064
-7.250 -0.1870 0.01780 0.01282 -0.1247 0.7658 0.0067
-7.000 -0.1655 0.01659 0.01138 -0.1241 0.7619 0.0068
-6.750 -0.1422 0.01565 0.01033 -0.1236 0.7586 0.0070
-6.500 -0.1183 0.01475 0.00930 -0.1232 0.7551 0.0071
-6.250 -0.0941 0.01394 0.00835 -0.1228 0.7517 0.0072
-6.000 -0.0696 0.01318 0.00745 -0.1224 0.7481 0.0072
-5.750 -0.0445 0.01256 0.00675 -0.1221 0.7450 0.0073
-5.500 -0.0194 0.01195 0.00607 -0.1218 0.7418 0.0074
-5.250 0.0060 0.01142 0.00549 -0.1215 0.7386 0.0076
-5.000 0.0323 0.01110 0.00510 -0.1214 0.7354 0.0081
-4.750 0.0584 0.01073 0.00466 -0.1213 0.7320 0.0083
-4.500 0.0848 0.01037 0.00427 -0.1212 0.7293 0.0085
-4.250 0.1113 0.00999 0.00385 -0.1211 0.7262 0.0086
-4.000 0.1374 0.00950 0.00331 -0.1210 0.7231 0.0090
-3.750 0.1645 0.00923 0.00299 -0.1210 0.7200 0.0099
-3.500 0.1922 0.00900 0.00270 -0.1211 0.7166 0.0129
-3.250 0.2191 0.00857 0.00242 -0.1212 0.7139 0.0433
-3.000 0.2466 0.00831 0.00229 -0.1214 0.7108 0.0752
-2.750 0.2741 0.00803 0.00216 -0.1217 0.7076 0.1256
-2.500 0.3011 0.00755 0.00203 -0.1222 0.7042 0.2359
-2.250 0.3278 0.00660 0.00185 -0.1231 0.7007 0.4863
-2.000 0.3554 0.00606 0.00185 -0.1235 0.6976 0.6680
-1.750 0.3840 0.00605 0.00188 -0.1237 0.6943 0.6973
-1.500 0.4127 0.00609 0.00189 -0.1239 0.6910 0.7127
-1.250 0.4412 0.00616 0.00192 -0.1241 0.6876 0.7273
-1.000 0.4702 0.00623 0.00194 -0.1244 0.6845 0.7371
-0.750 0.4984 0.00626 0.00199 -0.1245 0.6811 0.7444
-0.500 0.5272 0.00632 0.00200 -0.1248 0.6776 0.7512
-0.250 0.5552 0.00637 0.00204 -0.1249 0.6739 0.7577
0.000 0.5833 0.00648 0.00212 -0.1250 0.6700 0.7660
0.250 0.6108 0.00653 0.00220 -0.1249 0.6659 0.7742
0.500 0.6386 0.00662 0.00228 -0.1249 0.6617 0.7814
0.750 0.6668 0.00668 0.00229 -0.1251 0.6576 0.7847
1.000 0.6949 0.00669 0.00230 -0.1253 0.6535 0.7867
1.250 0.7230 0.00670 0.00232 -0.1255 0.6491 0.7886
1.500 0.7508 0.00674 0.00234 -0.1257 0.6443 0.7904
1.750 0.7786 0.00680 0.00237 -0.1258 0.6395 0.7924
2.000 0.8067 0.00682 0.00240 -0.1261 0.6342 0.7944
2.250 0.8343 0.00687 0.00242 -0.1262 0.6289 0.7963
2.500 0.8621 0.00693 0.00246 -0.1264 0.6237 0.7979
2.750 0.8898 0.00696 0.00250 -0.1266 0.6177 0.7997
3.000 0.9164 0.00703 0.00255 -0.1265 0.6118 0.8016
3.250 0.9439 0.00706 0.00261 -0.1266 0.6055 0.8034
3.500 0.9704 0.00714 0.00267 -0.1265 0.5986 0.8052
3.750 0.9973 0.00720 0.00275 -0.1266 0.5917 0.8071
4.000 1.0234 0.00729 0.00283 -0.1264 0.5837 0.8091
4.250 1.0499 0.00738 0.00291 -0.1264 0.5753 0.8111
4.500 1.0751 0.00751 0.00302 -0.1261 0.5661 0.8132
4.750 1.1009 0.00761 0.00311 -0.1259 0.5560 0.8151
5.000 1.1257 0.00772 0.00322 -0.1256 0.5452 0.8172
5.250 1.1497 0.00787 0.00336 -0.1250 0.5336 0.8192
5.500 1.1730 0.00804 0.00352 -0.1244 0.5208 0.8213
5.750 1.1957 0.00824 0.00368 -0.1236 0.5062 0.8236
6.000 1.2178 0.00846 0.00387 -0.1228 0.4903 0.8260
6.250 1.2388 0.00872 0.00408 -0.1217 0.4723 0.8285
6.500 1.2578 0.00901 0.00431 -0.1203 0.4520 0.8311
6.750 1.2746 0.00935 0.00459 -0.1184 0.4323 0.8338
7.000 1.2905 0.00965 0.00485 -0.1163 0.4136 0.8365
7.250 1.3038 0.01004 0.00517 -0.1138 0.3919 0.8397
7.500 1.3165 0.01049 0.00554 -0.1112 0.3701 0.8429
7.750 1.3290 0.01096 0.00593 -0.1087 0.3481 0.8462
8.000 1.3397 0.01148 0.00639 -0.1059 0.3272 0.8500
8.250 1.3509 0.01202 0.00687 -0.1033 0.3050 0.8541
8.750 1.3705 0.01327 0.00797 -0.0978 0.2642 0.8626
9.000 1.3777 0.01402 0.00865 -0.0948 0.2420 0.8677
9.250 1.3849 0.01484 0.00939 -0.0919 0.2208 0.8733
9.500 1.3889 0.01582 0.01028 -0.0887 0.1970 0.8796
9.750 1.3965 0.01669 0.01111 -0.0861 0.1798 0.8872
10.000 1.3995 0.01780 0.01214 -0.0830 0.1570 0.8973
10.250 1.4034 0.01887 0.01318 -0.0801 0.1395 0.9119
10.500 1.4074 0.01989 0.01423 -0.0773 0.1221 0.9638
10.750 1.4158 0.02103 0.01532 -0.0756 0.1086 1.0000
11.000 1.4230 0.02232 0.01655 -0.0738 0.0946 1.0000
11.250 1.4301 0.02365 0.01782 -0.0720 0.0821 1.0000
11.500 1.4360 0.02508 0.01920 -0.0703 0.0697 1.0000
11.750 1.4429 0.02650 0.02057 -0.0687 0.0598 1.0000
12.000 1.4497 0.02796 0.02201 -0.0672 0.0511 1.0000
12.250 1.4553 0.02955 0.02357 -0.0657 0.0427 1.0000
12.500 1.4609 0.03119 0.02518 -0.0642 0.0357 1.0000
12.750 1.4666 0.03287 0.02685 -0.0629 0.0296 1.0000
13.000 1.4738 0.03447 0.02846 -0.0618 0.0252 1.0000
13.250 1.4798 0.03622 0.03022 -0.0607 0.0211 1.0000
13.500 1.4858 0.03801 0.03203 -0.0597 0.0181 1.0000
13.750 1.4920 0.03984 0.03387 -0.0588 0.0151 1.0000
14.000 1.4983 0.04170 0.03578 -0.0579 0.0132 1.0000
14.250 1.5028 0.04376 0.03786 -0.0571 0.0108 1.0000
14.500 1.5092 0.04570 0.03985 -0.0565 0.0095 1.0000
14.750 1.5135 0.04791 0.04211 -0.0558 0.0080 1.0000
15.000 1.5168 0.05027 0.04450 -0.0552 0.0060 1.0000
15.250 1.5222 0.05247 0.04677 -0.0548 0.0054 1.0000
15.500 1.5219 0.05535 0.04969 -0.0544 0.0035 1.0000
15.750 1.5220 0.05826 0.05267 -0.0540 0.0024 1.0000
16.000 1.5182 0.06176 0.05625 -0.0537 0.0014 1.0000
16.250 1.5211 0.06450 0.05907 -0.0537 0.0014 1.0000
16.500 1.5153 0.06841 0.06309 -0.0538 0.0010 1.0000
16.750 1.5157 0.07164 0.06641 -0.0540 0.0009 1.0000
17.000 1.5150 0.07508 0.06995 -0.0544 0.0008 1.0000
17.250 1.5143 0.07860 0.07358 -0.0549 0.0008 1.0000
17.500 1.5122 0.08237 0.07745 -0.0556 0.0007 1.0000
17.750 1.5081 0.08651 0.08171 -0.0564 0.0007 1.0000
18.000 1.5066 0.09037 0.08566 -0.0574 0.0007 1.0000
18.250 1.5006 0.09499 0.09040 -0.0586 0.0006 1.0000
18.500 1.4950 0.09964 0.09516 -0.0600 0.0006 1.0000
18.750 1.4870 0.10474 0.10037 -0.0617 0.0006 1.0000
19.000 1.4807 0.10966 0.10541 -0.0635 0.0006 1.0000
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Polar data table (+)
Polar graphs
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