EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 500,000 Max Cl/Cd: 99.29 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e553-il-500000.txt Download as CSV file: xf-e553-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 553 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.5667 0.12927 0.12652 -0.0451 1.0000 0.0094
-16.750 -0.6028 0.11667 0.11377 -0.0515 1.0000 0.0092
-16.500 -0.6288 0.10707 0.10403 -0.0565 1.0000 0.0090
-16.250 -0.6551 0.09797 0.09476 -0.0613 1.0000 0.0089
-16.000 -0.6730 0.09104 0.08770 -0.0648 1.0000 0.0088
-15.750 -0.6922 0.08421 0.08070 -0.0682 1.0000 0.0087
-15.500 -0.7094 0.07809 0.07441 -0.0710 1.0000 0.0086
-15.250 -0.7243 0.07261 0.06876 -0.0733 1.0000 0.0086
-15.000 -0.7350 0.06803 0.06402 -0.0750 1.0000 0.0085
-14.750 -0.7455 0.06365 0.05949 -0.0765 1.0000 0.0086
-14.500 -0.7510 0.06015 0.05585 -0.0773 1.0000 0.0084
-14.250 -0.7562 0.05682 0.05239 -0.0781 1.0000 0.0086
-14.000 -0.7593 0.05389 0.04933 -0.0784 1.0000 0.0086
-13.750 -0.7621 0.05116 0.04648 -0.0784 1.0000 0.0087
-13.500 -0.7627 0.04880 0.04402 -0.0781 1.0000 0.0087
-13.250 -0.7621 0.04668 0.04181 -0.0776 1.0000 0.0087
-13.000 -0.7613 0.04467 0.03971 -0.0770 1.0000 0.0089
-12.750 -0.7608 0.04272 0.03767 -0.0762 1.0000 0.0091
-12.500 -0.7583 0.04113 0.03602 -0.0750 1.0000 0.0090
-12.250 -0.7580 0.03945 0.03426 -0.0737 1.0000 0.0092
-12.000 -0.7587 0.03795 0.03270 -0.0720 1.0000 0.0093
-11.750 -0.7627 0.03665 0.03138 -0.0695 1.0000 0.0093
-11.500 -0.7492 0.03503 0.02968 -0.0705 0.9985 0.0095
-11.250 -0.7291 0.03266 0.02730 -0.0737 0.9946 0.0101
-11.000 -0.7052 0.03077 0.02537 -0.0768 0.9894 0.0102
-10.750 -0.6802 0.02886 0.02341 -0.0803 0.9835 0.0106
-10.500 -0.6586 0.02709 0.02159 -0.0828 0.9736 0.0111
-10.250 -0.6373 0.02531 0.01975 -0.0853 0.9630 0.0115
-9.750 -0.5838 0.02109 0.01537 -0.0938 0.9454 0.0128
-9.500 -0.5478 0.01933 0.01353 -0.0994 0.9358 0.0142
-9.250 -0.5128 0.01766 0.01174 -0.1045 0.9239 0.0158
-9.000 -0.4805 0.01678 0.01076 -0.1072 0.9108 0.0184
-8.750 -0.4592 0.01587 0.00978 -0.1078 0.8951 0.0216
-8.500 -0.4413 0.01511 0.00893 -0.1073 0.8802 0.0267
-8.250 -0.4245 0.01436 0.00816 -0.1064 0.8667 0.0347
-8.000 -0.4051 0.01374 0.00753 -0.1057 0.8547 0.0455
-7.750 -0.3849 0.01310 0.00692 -0.1052 0.8440 0.0631
-7.500 -0.3648 0.01246 0.00635 -0.1046 0.8332 0.0893
-7.250 -0.3448 0.01170 0.00575 -0.1041 0.8231 0.1296
-7.000 -0.3252 0.01071 0.00501 -0.1038 0.8139 0.1979
-6.750 -0.3070 0.00951 0.00430 -0.1034 0.8040 0.3142
-6.500 -0.2809 0.00925 0.00414 -0.1034 0.7958 0.3663
-6.250 -0.2536 0.00922 0.00407 -0.1034 0.7868 0.3905
-6.000 -0.2254 0.00926 0.00402 -0.1034 0.7789 0.4055
-5.750 -0.1978 0.00927 0.00399 -0.1034 0.7704 0.4155
-5.500 -0.1693 0.00933 0.00390 -0.1035 0.7627 0.4241
-5.250 -0.1415 0.00937 0.00392 -0.1034 0.7542 0.4323
-5.000 -0.1131 0.00947 0.00388 -0.1035 0.7469 0.4405
-4.750 -0.0853 0.00949 0.00390 -0.1034 0.7388 0.4465
-4.500 -0.0568 0.00962 0.00389 -0.1035 0.7315 0.4534
-4.250 -0.0291 0.00970 0.00399 -0.1034 0.7234 0.4616
-4.000 -0.0007 0.00983 0.00402 -0.1034 0.7163 0.4680
-3.750 0.0275 0.00982 0.00392 -0.1036 0.7086 0.4708
-3.500 0.0555 0.00973 0.00377 -0.1036 0.7014 0.4736
-3.250 0.0835 0.00969 0.00371 -0.1037 0.6939 0.4762
-3.000 0.1116 0.00968 0.00363 -0.1037 0.6866 0.4786
-2.750 0.1399 0.00968 0.00357 -0.1038 0.6798 0.4814
-2.500 0.1680 0.00967 0.00351 -0.1039 0.6723 0.4844
-2.250 0.1964 0.00971 0.00343 -0.1041 0.6655 0.4870
-2.000 0.2243 0.00963 0.00334 -0.1041 0.6582 0.4895
-1.750 0.2523 0.00963 0.00329 -0.1042 0.6516 0.4919
-1.500 0.2803 0.00961 0.00328 -0.1042 0.6444 0.4946
-1.250 0.3083 0.00964 0.00325 -0.1043 0.6375 0.4975
-1.000 0.3365 0.00967 0.00324 -0.1044 0.6309 0.5005
-0.750 0.3645 0.00969 0.00321 -0.1045 0.6240 0.5031
-0.500 0.3924 0.00970 0.00316 -0.1046 0.6176 0.5057
-0.250 0.4202 0.00967 0.00317 -0.1046 0.6107 0.5083
0.000 0.4480 0.00972 0.00318 -0.1046 0.6045 0.5112
0.250 0.4759 0.00976 0.00321 -0.1047 0.5979 0.5144
0.500 0.5037 0.00980 0.00322 -0.1047 0.5913 0.5175
0.750 0.5316 0.00989 0.00324 -0.1048 0.5854 0.5203
1.000 0.5592 0.00986 0.00325 -0.1048 0.5790 0.5233
1.250 0.5867 0.00991 0.00329 -0.1048 0.5729 0.5262
1.500 0.6143 0.00996 0.00335 -0.1048 0.5668 0.5294
1.750 0.6418 0.01002 0.00341 -0.1048 0.5606 0.5330
2.000 0.6694 0.01014 0.00347 -0.1049 0.5550 0.5364
2.250 0.6967 0.01014 0.00353 -0.1049 0.5489 0.5397
2.500 0.7239 0.01019 0.00360 -0.1048 0.5429 0.5431
2.750 0.7511 0.01031 0.00369 -0.1048 0.5373 0.5466
3.000 0.7783 0.01035 0.00378 -0.1047 0.5310 0.5504
3.250 0.8052 0.01047 0.00385 -0.1046 0.5250 0.5541
3.500 0.8320 0.01052 0.00397 -0.1045 0.5192 0.5582
3.750 0.8586 0.01059 0.00408 -0.1044 0.5130 0.5624
4.000 0.8852 0.01073 0.00419 -0.1042 0.5072 0.5669
4.250 0.9119 0.01081 0.00431 -0.1041 0.5014 0.5711
4.500 0.9381 0.01087 0.00444 -0.1039 0.4954 0.5755
4.750 0.9641 0.01103 0.00459 -0.1037 0.4896 0.5803
5.000 0.9901 0.01110 0.00472 -0.1034 0.4830 0.5858
5.250 1.0154 0.01122 0.00486 -0.1030 0.4765 0.5910
5.500 1.0409 0.01132 0.00503 -0.1027 0.4701 0.5966
5.750 1.0662 0.01145 0.00518 -0.1023 0.4635 0.6027
6.000 1.0908 0.01159 0.00536 -0.1019 0.4572 0.6085
6.250 1.1155 0.01168 0.00554 -0.1014 0.4498 0.6152
6.500 1.1390 0.01188 0.00572 -0.1007 0.4427 0.6223
6.750 1.1633 0.01196 0.00592 -0.1002 0.4352 0.6300
7.000 1.1859 0.01216 0.00612 -0.0993 0.4278 0.6383
7.250 1.2093 0.01227 0.00635 -0.0986 0.4199 0.6471
7.500 1.2307 0.01249 0.00657 -0.0976 0.4120 0.6563
7.750 1.2530 0.01262 0.00681 -0.0967 0.4032 0.6667
8.000 1.2726 0.01284 0.00707 -0.0953 0.3942 0.6777
8.250 1.2918 0.01301 0.00732 -0.0939 0.3846 0.6903
8.500 1.3091 0.01322 0.00760 -0.0921 0.3747 0.7045
8.750 1.3241 0.01351 0.00793 -0.0899 0.3636 0.7203
9.000 1.3399 0.01379 0.00829 -0.0879 0.3512 0.7385
9.250 1.3543 0.01412 0.00869 -0.0857 0.3377 0.7600
9.500 1.3661 0.01452 0.00915 -0.0832 0.3224 0.7868
9.750 1.3752 0.01495 0.00968 -0.0801 0.3066 0.8255
10.000 1.3795 0.01523 0.01016 -0.0762 0.2907 1.0000
10.250 1.3876 0.01602 0.01088 -0.0736 0.2729 1.0000
10.500 1.3948 0.01689 0.01168 -0.0710 0.2538 1.0000
10.750 1.3994 0.01794 0.01265 -0.0682 0.2340 1.0000
11.000 1.4022 0.01916 0.01378 -0.0654 0.2151 1.0000
11.250 1.4038 0.02053 0.01506 -0.0627 0.1973 1.0000
11.500 1.4065 0.02193 0.01640 -0.0604 0.1809 1.0000
11.750 1.4085 0.02346 0.01788 -0.0581 0.1657 1.0000
12.000 1.4097 0.02513 0.01951 -0.0561 0.1515 1.0000
12.250 1.4106 0.02692 0.02126 -0.0542 0.1386 1.0000
12.500 1.4109 0.02885 0.02315 -0.0524 0.1266 1.0000
12.750 1.4125 0.03076 0.02505 -0.0509 0.1156 1.0000
13.000 1.4136 0.03281 0.02710 -0.0496 0.1059 1.0000
13.250 1.4132 0.03506 0.02933 -0.0484 0.0970 1.0000
13.500 1.4120 0.03748 0.03174 -0.0473 0.0885 1.0000
13.750 1.4130 0.03980 0.03409 -0.0465 0.0810 1.0000
14.000 1.4115 0.04244 0.03672 -0.0457 0.0738 1.0000
14.250 1.4102 0.04515 0.03946 -0.0451 0.0673 1.0000
14.500 1.4100 0.04786 0.04220 -0.0447 0.0617 1.0000
14.750 1.4069 0.05097 0.04531 -0.0445 0.0561 1.0000
15.000 1.4068 0.05383 0.04822 -0.0443 0.0514 1.0000
15.250 1.4029 0.05721 0.05162 -0.0443 0.0472 1.0000
15.500 1.4025 0.06030 0.05477 -0.0445 0.0433 1.0000
15.750 1.3992 0.06380 0.05829 -0.0448 0.0400 1.0000
16.000 1.3968 0.06727 0.06183 -0.0452 0.0370 1.0000
16.250 1.3952 0.07073 0.06534 -0.0457 0.0342 1.0000
16.500 1.3879 0.07505 0.06969 -0.0465 0.0319 1.0000
16.750 1.3896 0.07820 0.07293 -0.0472 0.0295 1.0000
17.000 1.3859 0.08217 0.07695 -0.0481 0.0278 1.0000
17.250 1.3787 0.08674 0.08158 -0.0493 0.0260 1.0000
17.500 1.3795 0.09020 0.08513 -0.0503 0.0244 1.0000
17.750 1.3760 0.09433 0.08933 -0.0516 0.0229 1.0000
18.000 1.3683 0.09920 0.09424 -0.0532 0.0216 1.0000
18.250 1.3679 0.10301 0.09815 -0.0545 0.0204 1.0000
18.500 1.3655 0.10715 0.10237 -0.0560 0.0194 1.0000
18.750 1.3612 0.11163 0.10691 -0.0578 0.0183 1.0000
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Polar data table (+)
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