EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.18 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e583-il-1000000.txt Download as CSV file: xf-e583-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 583 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0644 0.08377 0.08083 -0.1206 0.7385 0.0096
-10.750 -0.0646 0.08012 0.07716 -0.1221 0.7329 0.0096
-10.500 -0.0649 0.07650 0.07354 -0.1236 0.7283 0.0097
-10.250 -0.0670 0.07253 0.06959 -0.1255 0.7237 0.0098
-10.000 -0.0724 0.06805 0.06510 -0.1277 0.7191 0.0100
-9.750 -0.0898 0.06043 0.05749 -0.1330 0.7148 0.0099
-9.500 -0.1297 0.05090 0.04789 -0.1383 0.7112 0.0098
-8.250 -0.2772 0.02413 0.01942 -0.1157 0.6924 0.0073
-8.000 -0.2601 0.02331 0.01852 -0.1146 0.6892 0.0075
-7.750 -0.2632 0.01749 0.01185 -0.1098 0.6863 0.0055
-7.500 -0.2433 0.01638 0.01054 -0.1087 0.6831 0.0055
-7.250 -0.2219 0.01543 0.00945 -0.1078 0.6806 0.0055
-7.000 -0.1994 0.01470 0.00862 -0.1071 0.6781 0.0057
-6.750 -0.1766 0.01403 0.00787 -0.1064 0.6754 0.0057
-6.500 -0.1530 0.01353 0.00729 -0.1058 0.6726 0.0061
-6.250 -0.1293 0.01307 0.00675 -0.1052 0.6700 0.0064
-6.000 -0.1050 0.01269 0.00629 -0.1047 0.6672 0.0067
-5.750 -0.0799 0.01239 0.00592 -0.1044 0.6649 0.0069
-5.500 -0.0579 0.01170 0.00521 -0.1036 0.6628 0.0075
-5.250 -0.0329 0.01136 0.00484 -0.1033 0.6604 0.0078
-5.000 -0.0073 0.01110 0.00455 -0.1030 0.6581 0.0083
-4.750 0.0184 0.01084 0.00426 -0.1028 0.6557 0.0087
-4.500 0.0443 0.01062 0.00399 -0.1026 0.6533 0.0091
-4.250 0.0696 0.01033 0.00364 -0.1023 0.6505 0.0100
-4.000 0.0961 0.01013 0.00344 -0.1022 0.6486 0.0113
-3.750 0.1225 0.00989 0.00320 -0.1020 0.6467 0.0146
-3.500 0.1477 0.00951 0.00294 -0.1018 0.6445 0.0355
-3.250 0.1739 0.00926 0.00279 -0.1017 0.6423 0.0596
-3.000 0.2002 0.00902 0.00266 -0.1017 0.6402 0.0911
-2.750 0.2263 0.00876 0.00254 -0.1017 0.6380 0.1384
-2.500 0.2512 0.00832 0.00243 -0.1017 0.6356 0.2376
-2.250 0.2754 0.00768 0.00229 -0.1017 0.6332 0.3965
-2.000 0.2977 0.00661 0.00215 -0.1015 0.6315 0.6721
-1.750 0.3256 0.00658 0.00223 -0.1016 0.6294 0.7265
-1.500 0.3543 0.00661 0.00226 -0.1018 0.6272 0.7441
-1.250 0.3832 0.00667 0.00228 -0.1020 0.6250 0.7574
-1.000 0.4115 0.00674 0.00234 -0.1021 0.6228 0.7674
-0.750 0.4402 0.00683 0.00238 -0.1024 0.6203 0.7755
-0.500 0.4689 0.00696 0.00247 -0.1026 0.6175 0.7813
-0.250 0.4974 0.00701 0.00251 -0.1029 0.6157 0.7869
0.000 0.5255 0.00707 0.00257 -0.1029 0.6136 0.7937
0.250 0.5527 0.00723 0.00276 -0.1027 0.6112 0.8040
0.500 0.5797 0.00733 0.00287 -0.1025 0.6088 0.8116
0.750 0.6075 0.00741 0.00293 -0.1025 0.6064 0.8151
1.000 0.6360 0.00747 0.00295 -0.1029 0.6037 0.8170
1.250 0.6649 0.00754 0.00299 -0.1033 0.6009 0.8187
1.500 0.6934 0.00754 0.00299 -0.1037 0.5987 0.8201
1.750 0.7219 0.00755 0.00300 -0.1040 0.5959 0.8216
2.000 0.7504 0.00758 0.00301 -0.1044 0.5930 0.8228
2.250 0.7785 0.00758 0.00300 -0.1047 0.5898 0.8241
2.500 0.8064 0.00765 0.00302 -0.1049 0.5862 0.8254
2.750 0.8340 0.00764 0.00306 -0.1051 0.5834 0.8266
3.000 0.8616 0.00765 0.00309 -0.1053 0.5799 0.8281
3.250 0.8890 0.00768 0.00312 -0.1054 0.5762 0.8295
3.500 0.9162 0.00773 0.00315 -0.1056 0.5724 0.8309
3.750 0.9435 0.00779 0.00322 -0.1057 0.5686 0.8323
4.000 0.9710 0.00781 0.00326 -0.1059 0.5647 0.8337
4.250 0.9981 0.00785 0.00331 -0.1060 0.5602 0.8351
4.500 1.0243 0.00793 0.00337 -0.1060 0.5554 0.8366
4.750 1.0515 0.00797 0.00344 -0.1062 0.5507 0.8379
5.000 1.0782 0.00803 0.00350 -0.1062 0.5452 0.8392
5.500 1.1294 0.00814 0.00364 -0.1059 0.5333 0.8425
5.750 1.1538 0.00823 0.00374 -0.1055 0.5264 0.8440
6.000 1.1787 0.00832 0.00385 -0.1052 0.5191 0.8456
6.250 1.2018 0.00844 0.00397 -0.1046 0.5105 0.8472
6.500 1.2256 0.00856 0.00410 -0.1041 0.5013 0.8490
6.750 1.2472 0.00873 0.00425 -0.1032 0.4916 0.8508
7.000 1.2687 0.00891 0.00442 -0.1023 0.4811 0.8527
7.250 1.2887 0.00910 0.00459 -0.1011 0.4704 0.8546
7.500 1.3055 0.00930 0.00478 -0.0993 0.4593 0.8568
7.750 1.3200 0.00956 0.00502 -0.0970 0.4470 0.8592
8.000 1.3339 0.00989 0.00532 -0.0947 0.4322 0.8616
8.250 1.3481 0.01022 0.00563 -0.0925 0.4179 0.8641
8.500 1.3623 0.01058 0.00597 -0.0903 0.4040 0.8667
8.750 1.3743 0.01101 0.00636 -0.0879 0.3891 0.8694
9.000 1.3857 0.01147 0.00679 -0.0854 0.3744 0.8720
9.250 1.3936 0.01202 0.00731 -0.0823 0.3579 0.8754
9.500 1.4011 0.01262 0.00789 -0.0793 0.3424 0.8789
9.750 1.4069 0.01335 0.00857 -0.0762 0.3262 0.8830
10.000 1.4105 0.01423 0.00940 -0.0730 0.3091 0.8869
10.250 1.4129 0.01517 0.01031 -0.0697 0.2922 0.8915
10.500 1.4144 0.01626 0.01136 -0.0665 0.2745 0.8965
10.750 1.4165 0.01745 0.01251 -0.0636 0.2582 0.9017
11.000 1.4171 0.01872 0.01376 -0.0607 0.2418 0.9080
11.250 1.4179 0.02009 0.01510 -0.0580 0.2264 0.9154
11.500 1.4188 0.02145 0.01647 -0.0554 0.2129 0.9253
11.750 1.4161 0.02303 0.01805 -0.0524 0.1961 0.9451
12.000 1.4209 0.02486 0.01985 -0.0516 0.1778 1.0000
12.250 1.4273 0.02635 0.02132 -0.0504 0.1677 1.0000
12.500 1.4264 0.02836 0.02326 -0.0486 0.1510 1.0000
12.750 1.4230 0.03062 0.02541 -0.0467 0.1334 1.0000
13.000 1.4268 0.03241 0.02717 -0.0455 0.1224 1.0000
13.250 1.4275 0.03448 0.02918 -0.0441 0.1097 1.0000
13.500 1.4266 0.03675 0.03139 -0.0428 0.0964 1.0000
13.750 1.4256 0.03909 0.03367 -0.0416 0.0836 1.0000
14.000 1.4275 0.04123 0.03578 -0.0406 0.0737 1.0000
14.250 1.4292 0.04347 0.03800 -0.0398 0.0650 1.0000
14.500 1.4342 0.04546 0.03999 -0.0391 0.0595 1.0000
14.750 1.4354 0.04786 0.04237 -0.0385 0.0523 1.0000
15.000 1.4370 0.05025 0.04475 -0.0379 0.0456 1.0000
15.250 1.4399 0.05258 0.04709 -0.0374 0.0398 1.0000
15.500 1.4425 0.05501 0.04953 -0.0371 0.0353 1.0000
15.750 1.4445 0.05753 0.05205 -0.0368 0.0308 1.0000
16.000 1.4465 0.06012 0.05467 -0.0366 0.0272 1.0000
16.250 1.4497 0.06262 0.05719 -0.0365 0.0241 1.0000
16.500 1.4504 0.06546 0.06005 -0.0365 0.0210 1.0000
16.750 1.4521 0.06825 0.06288 -0.0366 0.0186 1.0000
17.000 1.4547 0.07098 0.06566 -0.0368 0.0168 1.0000
17.500 1.4576 0.07684 0.07161 -0.0374 0.0134 1.0000
17.750 1.4577 0.08006 0.07488 -0.0379 0.0122 1.0000
18.000 1.4598 0.08302 0.07790 -0.0384 0.0111 1.0000
18.250 1.4591 0.08644 0.08138 -0.0390 0.0100 1.0000
18.500 1.4596 0.08971 0.08472 -0.0398 0.0092 1.0000
18.750 1.4595 0.09310 0.08817 -0.0406 0.0082 1.0000
19.000 1.4577 0.09682 0.09195 -0.0416 0.0074 1.0000
19.250 1.4575 0.10032 0.09554 -0.0426 0.0067 1.0000
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Polar data table (+)
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