EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 50,000 Max Cl/Cd: 11.87 at α=-1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e584-il-50000-n5.txt Download as CSV file: xf-e584-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 584 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1851 0.11044 0.10399 -0.0853 0.9347 0.0517
-10.250 -0.1707 0.10575 0.09927 -0.0892 0.9297 0.0494
-10.000 -0.1785 0.09842 0.09199 -0.0963 0.9210 0.0454
-9.750 -0.1637 0.09424 0.08775 -0.0997 0.9156 0.0444
-9.500 -0.1561 0.08967 0.08316 -0.1035 0.9087 0.0435
-9.250 -0.1533 0.08453 0.07800 -0.1082 0.9010 0.0425
-9.000 -0.1567 0.07868 0.07210 -0.1135 0.8937 0.0416
-8.750 -0.1696 0.07415 0.06749 -0.1160 0.8840 0.0407
-8.500 -0.1911 0.07036 0.06357 -0.1159 0.8741 0.0398
-8.250 -0.2218 0.06648 0.05935 -0.1139 0.8644 0.0386
-8.000 -0.2321 0.06461 0.05737 -0.1110 0.8558 0.0384
-7.750 -0.2385 0.06199 0.05454 -0.1090 0.8492 0.0383
-7.500 -0.2422 0.05952 0.05183 -0.1068 0.8434 0.0381
-7.250 -0.2509 0.05794 0.05005 -0.1029 0.8355 0.0380
-7.000 -0.2485 0.05514 0.04690 -0.1010 0.8308 0.0379
-6.750 -0.2511 0.05326 0.04471 -0.0976 0.8246 0.0379
-6.500 -0.2532 0.05158 0.04274 -0.0939 0.8184 0.0380
-6.250 -0.2448 0.04900 0.03958 -0.0917 0.8143 0.0386
-6.000 -0.2233 0.04724 0.03772 -0.0918 0.8116 0.0403
-5.750 -0.2310 0.04686 0.03719 -0.0867 0.8037 0.0411
-5.500 -0.2162 0.04517 0.03511 -0.0850 0.7995 0.0430
-5.250 -0.1925 0.04309 0.03244 -0.0842 0.7966 0.0449
-5.000 -0.1628 0.04126 0.03038 -0.0847 0.7945 0.0467
-4.750 -0.1704 0.04136 0.03042 -0.0793 0.7867 0.0478
-4.500 -0.1468 0.04030 0.02905 -0.0785 0.7830 0.0521
-4.250 -0.1158 0.03913 0.02779 -0.0789 0.7804 0.0577
-4.000 -0.0792 0.03799 0.02650 -0.0800 0.7784 0.0664
-3.750 -0.0831 0.03834 0.02675 -0.0750 0.7715 0.0711
-3.500 -0.0648 0.03789 0.02626 -0.0734 0.7671 0.0828
-3.250 -0.0398 0.03709 0.02551 -0.0730 0.7641 0.1039
-3.000 -0.0136 0.03600 0.02465 -0.0728 0.7618 0.1486
-2.750 -0.0274 0.03650 0.02531 -0.0667 0.7542 0.1716
-2.500 0.0144 0.03538 0.02724 -0.0642 0.7528 0.7321
-2.000 0.3411 0.03510 0.02493 -0.1068 0.7606 0.9781
-1.750 0.3668 0.03568 0.02536 -0.1085 0.7539 0.9918
-1.500 0.4066 0.03564 0.02506 -0.1121 0.7501 1.0000
-1.250 0.4251 0.03580 0.02505 -0.1112 0.7465 1.0000
-1.000 0.4211 0.03671 0.02588 -0.1068 0.7403 1.0000
-0.750 0.4149 0.03766 0.02678 -0.1021 0.7335 1.0000
-0.500 0.4340 0.03786 0.02682 -0.1011 0.7300 1.0000
-0.250 0.4189 0.03908 0.02800 -0.0951 0.7224 1.0000
0.000 0.4166 0.03985 0.02870 -0.0909 0.7163 1.0000
0.250 0.4401 0.03998 0.02868 -0.0905 0.7132 1.0000
0.500 0.4060 0.04165 0.03039 -0.0818 0.7034 1.0000
0.750 0.4220 0.04198 0.03060 -0.0803 0.6993 1.0000
1.000 0.4376 0.04233 0.03085 -0.0788 0.6954 1.0000
1.250 0.4159 0.04374 0.03225 -0.0722 0.6862 1.0000
1.500 0.4385 0.04390 0.03230 -0.0716 0.6830 1.0000
1.750 0.4187 0.04529 0.03369 -0.0654 0.6740 1.0000
2.000 0.4357 0.04562 0.03393 -0.0640 0.6698 1.0000
2.250 0.4618 0.04570 0.03391 -0.0638 0.6671 1.0000
2.500 0.4371 0.04724 0.03547 -0.0572 0.6569 1.0000
2.750 0.4609 0.04739 0.03553 -0.0566 0.6537 1.0000
3.000 0.4412 0.04882 0.03697 -0.0508 0.6441 1.0000
3.250 0.4608 0.04907 0.03716 -0.0496 0.6401 1.0000
3.500 0.4471 0.05032 0.03841 -0.0447 0.6313 1.0000
3.750 0.4620 0.05071 0.03875 -0.0431 0.6266 1.0000
4.000 0.4545 0.05177 0.03981 -0.0390 0.6184 1.0000
4.250 0.4657 0.05228 0.04028 -0.0370 0.6130 1.0000
4.750 0.4736 0.05381 0.04177 -0.0316 0.5993 1.0000
5.000 0.4991 0.05394 0.04188 -0.0313 0.5961 1.0000
5.250 0.4889 0.05542 0.04337 -0.0278 0.5857 1.0000
5.500 0.5156 0.05559 0.04353 -0.0277 0.5822 1.0000
5.750 0.5104 0.05718 0.04512 -0.0251 0.5721 1.0000
6.000 0.5371 0.05739 0.04533 -0.0251 0.5681 1.0000
6.250 0.5366 0.05898 0.04695 -0.0233 0.5584 1.0000
6.500 0.5613 0.05934 0.04735 -0.0232 0.5536 1.0000
6.750 0.5662 0.06079 0.04883 -0.0220 0.5446 1.0000
7.000 0.5873 0.06140 0.04946 -0.0218 0.5388 1.0000
7.250 0.6184 0.06139 0.04948 -0.0221 0.5353 1.0000
7.500 0.6153 0.06347 0.05161 -0.0207 0.5239 1.0000
7.750 0.6461 0.06347 0.05169 -0.0210 0.5203 1.0000
8.000 0.6444 0.06558 0.05386 -0.0198 0.5088 1.0000
8.250 0.6745 0.06558 0.05392 -0.0201 0.5049 1.0000
8.500 0.6740 0.06772 0.05613 -0.0191 0.4935 1.0000
8.750 0.7046 0.06764 0.05614 -0.0193 0.4895 1.0000
9.000 0.7034 0.06997 0.05855 -0.0185 0.4780 1.0000
9.250 0.7347 0.06974 0.05842 -0.0187 0.4740 1.0000
9.500 0.7331 0.07222 0.06098 -0.0180 0.4621 1.0000
9.750 0.7651 0.07184 0.06072 -0.0181 0.4582 1.0000
10.000 0.7626 0.07451 0.06348 -0.0175 0.4460 1.0000
10.250 0.7951 0.07397 0.06307 -0.0175 0.4422 1.0000
10.500 0.7919 0.07683 0.06602 -0.0170 0.4297 1.0000
10.750 0.8231 0.07631 0.06564 -0.0169 0.4256 1.0000
11.000 0.8212 0.07912 0.06855 -0.0166 0.4131 1.0000
11.500 0.8504 0.08139 0.07109 -0.0162 0.3966 1.0000
12.000 0.8801 0.08352 0.07349 -0.0157 0.3800 1.0000
12.250 0.8772 0.08678 0.07687 -0.0157 0.3675 1.0000
12.500 0.9099 0.08555 0.07582 -0.0152 0.3635 1.0000
12.750 0.9047 0.08921 0.07959 -0.0154 0.3504 1.0000
13.000 0.9389 0.08750 0.07806 -0.0147 0.3466 1.0000
13.250 0.9331 0.09135 0.08203 -0.0150 0.3336 1.0000
13.750 0.9629 0.09313 0.08414 -0.0146 0.3168 1.0000
14.250 0.9605 0.09993 0.09118 -0.0155 0.2938 1.0000
14.500 0.9851 0.09916 0.09062 -0.0148 0.2868 1.0000
15.000 1.0192 0.10004 0.09182 -0.0142 0.2699 1.0000
15.250 1.0061 0.10554 0.09742 -0.0156 0.2571 1.0000
15.750 1.0420 0.10595 0.09817 -0.0149 0.2397 1.0000
16.750 1.0424 0.11946 0.11215 -0.0186 0.1983 1.0000
17.000 1.0663 0.11835 0.11118 -0.0178 0.1896 1.0000
17.250 1.0826 0.11865 0.11159 -0.0177 0.1798 1.0000
17.500 1.0512 0.12835 0.12138 -0.0217 0.1701 1.0000
17.750 1.0803 0.12602 0.11915 -0.0204 0.1611 1.0000
18.000 1.0799 0.12961 0.12285 -0.0219 0.1519 1.0000
18.250 1.0544 0.13863 0.13195 -0.0261 0.1441 1.0000
18.500 1.0927 0.13405 0.12742 -0.0237 0.1344 1.0000
18.750 1.0399 0.14947 0.14292 -0.0314 0.1283 1.0000
19.000 1.0722 0.14584 0.13939 -0.0295 0.1200 1.0000
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