E392 (10.15%) (e392-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 500,000 Max Cl/Cd: 113.56 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e392-il-500000-n5.txt Download as CSV file: xf-e392-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3351 0.08954 0.08732 -0.0387 1.0000 0.0079
-8.750 -0.3349 0.08650 0.08431 -0.0394 1.0000 0.0077
-8.500 -0.3277 0.08256 0.08039 -0.0424 0.9898 0.0074
-8.250 -0.3140 0.07720 0.07504 -0.0488 0.9754 0.0071
-8.000 -0.2949 0.07053 0.06835 -0.0583 0.9509 0.0068
-7.500 -0.3331 0.02982 0.02652 -0.0957 0.8544 0.0055
-7.250 -0.3224 0.02456 0.02055 -0.0969 0.8342 0.0056
-7.000 -0.3039 0.02172 0.01722 -0.0971 0.8175 0.0057
-6.750 -0.2819 0.01986 0.01501 -0.0971 0.8028 0.0059
-6.500 -0.2583 0.01841 0.01324 -0.0970 0.7892 0.0061
-6.250 -0.2338 0.01714 0.01166 -0.0969 0.7767 0.0063
-6.000 -0.2085 0.01604 0.01028 -0.0968 0.7652 0.0066
-5.500 -0.1567 0.01423 0.00800 -0.0965 0.7437 0.0071
-5.250 -0.1301 0.01357 0.00717 -0.0964 0.7342 0.0075
-4.750 -0.0763 0.01253 0.00584 -0.0962 0.7161 0.0083
-4.500 -0.0497 0.01176 0.00491 -0.0961 0.7081 0.0086
-4.250 -0.0224 0.01124 0.00429 -0.0961 0.7000 0.0091
-4.000 0.0051 0.01086 0.00382 -0.0961 0.6927 0.0096
-3.750 0.0328 0.01054 0.00341 -0.0961 0.6852 0.0104
-3.500 0.0606 0.01028 0.00304 -0.0960 0.6786 0.0112
-3.250 0.0886 0.01003 0.00271 -0.0961 0.6717 0.0125
-3.000 0.1164 0.00982 0.00244 -0.0961 0.6654 0.0163
-2.750 0.1445 0.00951 0.00220 -0.0962 0.6592 0.0333
-2.500 0.1724 0.00932 0.00203 -0.0962 0.6531 0.0542
-2.250 0.2004 0.00911 0.00189 -0.0964 0.6473 0.0842
-2.000 0.2283 0.00885 0.00178 -0.0966 0.6414 0.1361
-1.750 0.2560 0.00857 0.00168 -0.0968 0.6363 0.2057
-1.500 0.2841 0.00835 0.00161 -0.0970 0.6306 0.2632
-1.250 0.3119 0.00814 0.00155 -0.0971 0.6250 0.3326
-1.000 0.3397 0.00791 0.00153 -0.0973 0.6201 0.4152
-0.750 0.3677 0.00775 0.00153 -0.0974 0.6147 0.4831
-0.500 0.3954 0.00765 0.00153 -0.0974 0.6094 0.5356
-0.250 0.4233 0.00756 0.00155 -0.0974 0.6045 0.5826
0.000 0.4510 0.00748 0.00157 -0.0974 0.5992 0.6295
0.250 0.4783 0.00742 0.00160 -0.0973 0.5942 0.6756
0.500 0.5055 0.00734 0.00164 -0.0971 0.5892 0.7238
0.750 0.5319 0.00725 0.00169 -0.0967 0.5839 0.7757
1.000 0.5566 0.00717 0.00175 -0.0958 0.5791 0.8335
1.250 0.5789 0.00705 0.00178 -0.0943 0.5740 0.9009
1.500 0.6117 0.00698 0.00176 -0.0952 0.5685 1.0000
1.750 0.6397 0.00707 0.00180 -0.0953 0.5634 1.0000
2.000 0.6679 0.00714 0.00186 -0.0954 0.5576 1.0000
2.250 0.6958 0.00724 0.00192 -0.0955 0.5515 1.0000
2.500 0.7238 0.00733 0.00199 -0.0955 0.5446 1.0000
2.750 0.7513 0.00744 0.00206 -0.0955 0.5365 1.0000
3.000 0.7791 0.00753 0.00215 -0.0955 0.5281 1.0000
3.250 0.8065 0.00766 0.00224 -0.0955 0.5198 1.0000
3.500 0.8341 0.00776 0.00235 -0.0955 0.5104 1.0000
3.750 0.8614 0.00789 0.00246 -0.0955 0.5007 1.0000
4.000 0.8885 0.00803 0.00258 -0.0954 0.4899 1.0000
4.500 0.9422 0.00835 0.00287 -0.0952 0.4651 1.0000
4.750 0.9687 0.00853 0.00303 -0.0950 0.4506 1.0000
5.000 0.9945 0.00878 0.00321 -0.0947 0.4278 1.0000
5.250 1.0184 0.00918 0.00346 -0.0942 0.3899 1.0000
5.500 1.0399 0.00982 0.00383 -0.0934 0.3327 1.0000
5.750 1.0610 0.01053 0.00427 -0.0925 0.2797 1.0000
6.500 1.1205 0.01297 0.00595 -0.0896 0.1311 1.0000
6.750 1.1415 0.01362 0.00647 -0.0887 0.1037 1.0000
7.000 1.1615 0.01433 0.00704 -0.0877 0.0767 1.0000
7.250 1.1812 0.01504 0.00762 -0.0867 0.0540 1.0000
7.500 1.2003 0.01577 0.00827 -0.0855 0.0349 1.0000
7.750 1.2179 0.01658 0.00899 -0.0842 0.0183 1.0000
8.000 1.2367 0.01726 0.00965 -0.0830 0.0137 1.0000
8.250 1.2565 0.01782 0.01026 -0.0819 0.0124 1.0000
8.500 1.2752 0.01843 0.01093 -0.0806 0.0115 1.0000
8.750 1.2924 0.01910 0.01168 -0.0792 0.0107 1.0000
9.000 1.3079 0.01984 0.01249 -0.0775 0.0102 1.0000
9.250 1.3195 0.02065 0.01339 -0.0752 0.0098 1.0000
9.500 1.3315 0.02140 0.01422 -0.0730 0.0096 1.0000
9.750 1.3425 0.02224 0.01514 -0.0707 0.0094 1.0000
10.000 1.3522 0.02318 0.01617 -0.0685 0.0092 1.0000
10.250 1.3611 0.02422 0.01730 -0.0664 0.0090 1.0000
10.500 1.3696 0.02535 0.01853 -0.0644 0.0086 1.0000
10.750 1.3768 0.02663 0.01991 -0.0625 0.0084 1.0000
11.000 1.3841 0.02799 0.02135 -0.0608 0.0081 1.0000
11.250 1.3903 0.02952 0.02297 -0.0592 0.0079 1.0000
11.500 1.3951 0.03126 0.02481 -0.0578 0.0077 1.0000
11.750 1.3996 0.03311 0.02675 -0.0565 0.0075 1.0000
12.000 1.4033 0.03514 0.02888 -0.0554 0.0074 1.0000
12.250 1.4056 0.03738 0.03122 -0.0543 0.0072 1.0000
12.500 1.4069 0.03982 0.03376 -0.0535 0.0071 1.0000
12.750 1.4057 0.04262 0.03668 -0.0527 0.0069 1.0000
13.000 1.4038 0.04559 0.03977 -0.0520 0.0068 1.0000
13.250 1.3996 0.04893 0.04323 -0.0514 0.0067 1.0000
13.500 1.4023 0.05154 0.04596 -0.0512 0.0066 1.0000
13.750 1.4055 0.05417 0.04871 -0.0511 0.0065 1.0000
14.000 1.4081 0.05692 0.05159 -0.0512 0.0064 1.0000
14.250 1.4080 0.06009 0.05489 -0.0513 0.0063 1.0000
14.500 1.4098 0.06313 0.05806 -0.0517 0.0061 1.0000
14.750 1.4093 0.06656 0.06163 -0.0522 0.0059 1.0000
15.000 1.4077 0.07024 0.06545 -0.0529 0.0058 1.0000
15.250 1.4051 0.07420 0.06955 -0.0537 0.0057 1.0000
15.500 1.4022 0.07833 0.07382 -0.0548 0.0056 1.0000
15.750 1.3979 0.08279 0.07842 -0.0561 0.0055 1.0000
16.000 1.3932 0.08746 0.08324 -0.0577 0.0054 1.0000
16.250 1.3876 0.09240 0.08835 -0.0595 0.0053 1.0000
16.500 1.3817 0.09756 0.09365 -0.0616 0.0052 1.0000
16.750 1.3750 0.10298 0.09921 -0.0640 0.0052 1.0000
17.000 1.3680 0.10861 0.10498 -0.0666 0.0051 1.0000
17.250 1.3600 0.11456 0.11107 -0.0695 0.0050 1.0000
17.500 1.3520 0.12069 0.11733 -0.0727 0.0050 1.0000
17.750 1.3434 0.12706 0.12384 -0.0761 0.0049 1.0000
18.000 1.3348 0.13359 0.13050 -0.0798 0.0048 1.0000
18.250 1.3258 0.14036 0.13740 -0.0838 0.0048 1.0000
18.500 1.3165 0.14737 0.14453 -0.0880 0.0047 1.0000
18.750 1.3069 0.15462 0.15191 -0.0925 0.0047 1.0000
19.000 1.2968 0.16216 0.15958 -0.0973 0.0047 1.0000
19.250 1.2857 0.17017 0.16772 -0.1025 0.0047 1.0000
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Polar data table (+)
Polar graphs
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