EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 100,000 Max Cl/Cd: 46.2 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e554-il-100000-n5.txt Download as CSV file: xf-e554-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5361 0.11209 0.10644 -0.0467 1.0000 0.0203
-14.750 -0.5632 0.10210 0.09631 -0.0523 1.0000 0.0201
-14.500 -0.5823 0.09457 0.08866 -0.0564 1.0000 0.0198
-14.250 -0.6066 0.08667 0.08055 -0.0608 1.0000 0.0198
-14.000 -0.6230 0.08070 0.07440 -0.0638 1.0000 0.0197
-13.750 -0.6381 0.07527 0.06879 -0.0664 1.0000 0.0198
-13.500 -0.6529 0.07028 0.06357 -0.0684 1.0000 0.0200
-13.250 -0.6633 0.06611 0.05919 -0.0698 1.0000 0.0202
-13.000 -0.6693 0.06255 0.05543 -0.0707 1.0000 0.0204
-12.750 -0.6698 0.05995 0.05280 -0.0711 1.0000 0.0209
-12.500 -0.6695 0.05749 0.05030 -0.0713 1.0000 0.0215
-12.250 -0.6686 0.05506 0.04777 -0.0713 1.0000 0.0219
-12.000 -0.6675 0.05270 0.04529 -0.0711 1.0000 0.0227
-11.750 -0.6643 0.05044 0.04287 -0.0705 1.0000 0.0235
-11.500 -0.6583 0.04847 0.04071 -0.0696 1.0000 0.0241
-11.250 -0.6503 0.04697 0.03924 -0.0685 1.0000 0.0247
-11.000 -0.6432 0.04549 0.03776 -0.0674 1.0000 0.0253
-10.750 -0.6363 0.04405 0.03630 -0.0660 1.0000 0.0263
-10.500 -0.6291 0.04274 0.03494 -0.0644 1.0000 0.0274
-10.250 -0.6237 0.04145 0.03363 -0.0627 1.0000 0.0286
-10.000 -0.6224 0.04007 0.03231 -0.0611 1.0000 0.0298
-9.750 -0.6217 0.03882 0.03106 -0.0591 1.0000 0.0314
-9.500 -0.6232 0.03769 0.02992 -0.0566 1.0000 0.0330
-9.000 -0.5941 0.03447 0.02675 -0.0585 0.9761 0.0387
-8.750 -0.5752 0.03268 0.02494 -0.0605 0.9513 0.0431
-8.500 -0.5514 0.03067 0.02289 -0.0638 0.9307 0.0494
-8.250 -0.5219 0.02846 0.02067 -0.0683 0.9121 0.0598
-8.000 -0.4931 0.02640 0.01861 -0.0724 0.8925 0.0753
-7.750 -0.4672 0.02441 0.01667 -0.0757 0.8718 0.1003
-7.500 -0.4449 0.02239 0.01478 -0.0784 0.8511 0.1407
-7.250 -0.4268 0.02022 0.01297 -0.0803 0.8310 0.2154
-7.000 -0.4039 0.01938 0.01274 -0.0809 0.8128 0.3274
-6.750 -0.3737 0.01944 0.01266 -0.0815 0.7961 0.3777
-6.500 -0.3436 0.01975 0.01278 -0.0817 0.7802 0.4050
-6.250 -0.3142 0.02004 0.01283 -0.0819 0.7653 0.4252
-6.000 -0.2847 0.02045 0.01304 -0.0817 0.7516 0.4394
-5.750 -0.2566 0.02076 0.01318 -0.0813 0.7380 0.4512
-5.500 -0.2291 0.02097 0.01318 -0.0812 0.7254 0.4642
-5.250 -0.2004 0.02158 0.01370 -0.0803 0.7141 0.4739
-5.000 -0.1735 0.02164 0.01356 -0.0802 0.7025 0.4829
-4.750 -0.1462 0.02170 0.01351 -0.0797 0.6916 0.4874
-4.500 -0.1187 0.02149 0.01305 -0.0800 0.6821 0.4929
-4.250 -0.0919 0.02109 0.01243 -0.0805 0.6720 0.4983
-4.000 -0.0641 0.02105 0.01225 -0.0803 0.6641 0.5009
-3.750 -0.0375 0.02096 0.01206 -0.0802 0.6546 0.5041
-3.500 -0.0097 0.02079 0.01171 -0.0804 0.6470 0.5078
-3.250 0.0175 0.02055 0.01129 -0.0808 0.6383 0.5125
-3.000 0.0454 0.02035 0.01091 -0.0811 0.6310 0.5163
-2.750 0.0726 0.02029 0.01077 -0.0810 0.6238 0.5186
-2.500 0.0998 0.02023 0.01063 -0.0810 0.6169 0.5216
-2.250 0.1280 0.02016 0.01041 -0.0812 0.6113 0.5253
-2.000 0.1554 0.02005 0.01020 -0.0815 0.6042 0.5294
-1.750 0.1838 0.01991 0.00990 -0.0820 0.5979 0.5333
-1.500 0.2114 0.01990 0.00981 -0.0819 0.5927 0.5356
-1.250 0.2381 0.01990 0.00981 -0.0818 0.5863 0.5386
-1.000 0.2658 0.01990 0.00975 -0.0819 0.5810 0.5422
-0.750 0.2946 0.01989 0.00960 -0.0823 0.5767 0.5463
-0.500 0.3224 0.01986 0.00949 -0.0827 0.5711 0.5504
-0.250 0.3494 0.01988 0.00952 -0.0827 0.5657 0.5530
0.000 0.3771 0.01993 0.00952 -0.0827 0.5613 0.5560
0.250 0.4047 0.02000 0.00955 -0.0828 0.5570 0.5598
0.500 0.4318 0.02007 0.00963 -0.0829 0.5521 0.5642
0.750 0.4601 0.02013 0.00962 -0.0833 0.5477 0.5687
1.000 0.4876 0.02020 0.00969 -0.0833 0.5438 0.5715
1.250 0.5149 0.02031 0.00979 -0.0833 0.5398 0.5749
1.500 0.5411 0.02044 0.00998 -0.0832 0.5351 0.5790
1.750 0.5687 0.02057 0.01010 -0.0835 0.5311 0.5839
2.000 0.5965 0.02068 0.01020 -0.0836 0.5275 0.5882
2.250 0.6247 0.02081 0.01031 -0.0837 0.5244 0.5921
2.500 0.6494 0.02102 0.01064 -0.0834 0.5197 0.5965
2.750 0.6760 0.02120 0.01086 -0.0835 0.5155 0.6015
3.000 0.7030 0.02136 0.01105 -0.0835 0.5120 0.6060
3.250 0.7304 0.02152 0.01123 -0.0835 0.5088 0.6106
3.500 0.7565 0.02174 0.01152 -0.0834 0.5051 0.6161
3.750 0.7815 0.02202 0.01190 -0.0833 0.5008 0.6221
4.000 0.8065 0.02225 0.01224 -0.0829 0.4969 0.6267
4.250 0.8335 0.02244 0.01247 -0.0829 0.4935 0.6323
4.500 0.8627 0.02263 0.01263 -0.0833 0.4906 0.6391
4.750 0.8844 0.02298 0.01320 -0.0825 0.4862 0.6445
5.000 0.9079 0.02331 0.01366 -0.0821 0.4819 0.6513
5.250 0.9336 0.02355 0.01399 -0.0819 0.4781 0.6586
5.500 0.9608 0.02374 0.01423 -0.0818 0.4749 0.6654
5.750 0.9857 0.02408 0.01466 -0.0816 0.4711 0.6735
6.000 1.0058 0.02450 0.01531 -0.0806 0.4662 0.6807
6.250 1.0301 0.02481 0.01571 -0.0803 0.4620 0.6902
6.500 1.0568 0.02496 0.01595 -0.0801 0.4583 0.6990
6.750 1.0805 0.02531 0.01641 -0.0796 0.4541 0.7096
7.000 1.0980 0.02577 0.01711 -0.0783 0.4486 0.7195
7.250 1.1215 0.02599 0.01745 -0.0777 0.4439 0.7311
7.500 1.1502 0.02602 0.01753 -0.0777 0.4400 0.7448
7.750 1.1630 0.02660 0.01839 -0.0757 0.4338 0.7589
8.000 1.1822 0.02686 0.01882 -0.0744 0.4283 0.7753
8.500 1.2176 0.02733 0.01966 -0.0711 0.4175 0.8184
8.750 1.2309 0.02750 0.02005 -0.0687 0.4116 0.8527
9.000 1.2535 0.02713 0.01979 -0.0673 0.4067 0.9834
9.250 1.2620 0.02801 0.02089 -0.0653 0.3988 1.0000
9.500 1.2858 0.02813 0.02103 -0.0649 0.3922 1.0000
9.750 1.2953 0.02881 0.02184 -0.0628 0.3846 1.0000
10.000 1.3087 0.02918 0.02228 -0.0610 0.3772 1.0000
10.250 1.3156 0.02984 0.02305 -0.0584 0.3696 1.0000
10.500 1.3226 0.03050 0.02380 -0.0560 0.3613 1.0000
10.750 1.3248 0.03149 0.02491 -0.0534 0.3529 1.0000
11.000 1.3316 0.03226 0.02573 -0.0514 0.3440 1.0000
11.250 1.3240 0.03408 0.02770 -0.0488 0.3344 1.0000
11.500 1.3277 0.03531 0.02897 -0.0472 0.3248 1.0000
11.750 1.3221 0.03740 0.03115 -0.0455 0.3142 1.0000
12.000 1.3132 0.04007 0.03391 -0.0442 0.3033 1.0000
12.250 1.3093 0.04247 0.03634 -0.0433 0.2920 1.0000
12.500 1.3077 0.04478 0.03864 -0.0426 0.2801 1.0000
12.750 1.2986 0.04807 0.04197 -0.0422 0.2679 1.0000
13.000 1.2898 0.05151 0.04546 -0.0420 0.2558 1.0000
13.250 1.2835 0.05477 0.04872 -0.0420 0.2434 1.0000
13.500 1.2787 0.05793 0.05187 -0.0420 0.2312 1.0000
13.750 1.2745 0.06108 0.05499 -0.0420 0.2191 1.0000
14.000 1.2682 0.06469 0.05861 -0.0424 0.2072 1.0000
14.250 1.2619 0.06845 0.06240 -0.0430 0.1959 1.0000
14.500 1.2572 0.07207 0.06601 -0.0435 0.1849 1.0000
14.750 1.2537 0.07559 0.06950 -0.0441 0.1745 1.0000
15.000 1.2486 0.07951 0.07344 -0.0450 0.1642 1.0000
15.250 1.2443 0.08342 0.07739 -0.0460 0.1545 1.0000
15.500 1.2411 0.08719 0.08113 -0.0470 0.1455 1.0000
15.750 1.2369 0.09125 0.08523 -0.0482 0.1366 1.0000
16.000 1.2338 0.09522 0.08926 -0.0494 0.1283 1.0000
16.250 1.2306 0.09917 0.09316 -0.0507 0.1207 1.0000
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