S4053 (s4053-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.64 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4053-il-1000000-n5.txt Download as CSV file: xf-s4053-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4053
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4065 0.08776 0.08614 -0.0315 1.0000 0.0058
-8.750 -0.4103 0.08382 0.08222 -0.0326 1.0000 0.0057
-8.500 -0.4152 0.08013 0.07856 -0.0334 1.0000 0.0055
-8.000 -0.4089 0.06789 0.06635 -0.0471 0.9884 0.0054
-7.750 -0.3975 0.05851 0.05692 -0.0605 0.9785 0.0054
-7.500 -0.3808 0.04766 0.04589 -0.0731 0.9667 0.0056
-7.250 -0.3664 0.03562 0.03341 -0.0813 0.9461 0.0059
-7.000 -0.3586 0.02548 0.02255 -0.0828 0.9170 0.0063
-6.750 -0.3454 0.02137 0.01790 -0.0816 0.8914 0.0065
-6.500 -0.3283 0.01878 0.01486 -0.0803 0.8711 0.0066
-6.250 -0.3082 0.01696 0.01269 -0.0792 0.8540 0.0067
-6.000 -0.2859 0.01570 0.01115 -0.0784 0.8389 0.0068
-5.750 -0.2622 0.01479 0.01001 -0.0777 0.8250 0.0070
-5.500 -0.2380 0.01395 0.00897 -0.0771 0.8125 0.0071
-5.250 -0.2139 0.01298 0.00778 -0.0764 0.8007 0.0072
-4.750 -0.1641 0.01146 0.00594 -0.0753 0.7792 0.0073
-4.500 -0.1387 0.01088 0.00524 -0.0748 0.7695 0.0074
-4.250 -0.1128 0.01048 0.00473 -0.0744 0.7602 0.0075
-4.000 -0.0883 0.00966 0.00378 -0.0738 0.7509 0.0079
-3.750 -0.0628 0.00916 0.00318 -0.0733 0.7427 0.0085
-3.500 -0.0363 0.00891 0.00287 -0.0730 0.7341 0.0089
-3.250 -0.0095 0.00868 0.00260 -0.0728 0.7263 0.0094
-3.000 0.0172 0.00849 0.00234 -0.0725 0.7185 0.0098
-2.750 0.0442 0.00829 0.00208 -0.0723 0.7108 0.0102
-2.500 0.0711 0.00813 0.00186 -0.0721 0.7035 0.0106
-2.250 0.0984 0.00799 0.00168 -0.0719 0.6961 0.0111
-2.000 0.1255 0.00788 0.00152 -0.0717 0.6890 0.0116
-1.750 0.1529 0.00776 0.00136 -0.0716 0.6816 0.0118
-1.500 0.1801 0.00765 0.00119 -0.0714 0.6747 0.0127
-1.250 0.2075 0.00755 0.00107 -0.0712 0.6671 0.0160
-1.000 0.2342 0.00732 0.00097 -0.0710 0.6599 0.0633
-0.750 0.2606 0.00707 0.00090 -0.0708 0.6517 0.1324
-0.500 0.2870 0.00682 0.00085 -0.0706 0.6433 0.2120
-0.250 0.3125 0.00649 0.00084 -0.0703 0.6343 0.3323
0.000 0.3376 0.00607 0.00084 -0.0700 0.6252 0.4833
0.250 0.3637 0.00589 0.00085 -0.0697 0.6166 0.5624
0.500 0.3883 0.00562 0.00088 -0.0691 0.6073 0.6795
0.750 0.4123 0.00538 0.00092 -0.0682 0.5975 0.7792
1.000 0.4335 0.00509 0.00099 -0.0665 0.5869 0.9057
1.250 0.4738 0.00513 0.00105 -0.0691 0.5725 0.9687
1.500 0.5075 0.00523 0.00108 -0.0704 0.5568 0.9825
2.000 0.5759 0.00547 0.00116 -0.0733 0.5217 0.9947
2.250 0.6107 0.00562 0.00121 -0.0750 0.4990 0.9991
2.500 0.6370 0.00581 0.00129 -0.0748 0.4718 1.0000
2.750 0.6601 0.00605 0.00140 -0.0738 0.4414 1.0000
3.000 0.6831 0.00630 0.00151 -0.0729 0.4098 1.0000
3.250 0.7059 0.00658 0.00165 -0.0719 0.3762 1.0000
3.500 0.7286 0.00687 0.00180 -0.0710 0.3435 1.0000
3.750 0.7512 0.00719 0.00198 -0.0700 0.3098 1.0000
4.000 0.7740 0.00750 0.00216 -0.0691 0.2795 1.0000
4.250 0.7957 0.00791 0.00238 -0.0680 0.2384 1.0000
4.500 0.8180 0.00830 0.00260 -0.0671 0.2041 1.0000
4.750 0.8415 0.00859 0.00280 -0.0663 0.1822 1.0000
5.000 0.8649 0.00890 0.00303 -0.0656 0.1615 1.0000
5.250 0.8881 0.00923 0.00326 -0.0648 0.1394 1.0000
5.500 0.9111 0.00959 0.00352 -0.0640 0.1178 1.0000
5.750 0.9344 0.00991 0.00377 -0.0633 0.1010 1.0000
6.000 0.9579 0.01023 0.00403 -0.0626 0.0878 1.0000
6.250 0.9814 0.01054 0.00430 -0.0619 0.0767 1.0000
6.500 1.0047 0.01086 0.00460 -0.0612 0.0663 1.0000
6.750 1.0274 0.01124 0.00492 -0.0604 0.0541 1.0000
7.000 1.0499 0.01162 0.00525 -0.0595 0.0440 1.0000
7.250 1.0728 0.01197 0.00557 -0.0588 0.0379 1.0000
7.500 1.0960 0.01229 0.00589 -0.0581 0.0339 1.0000
7.750 1.1189 0.01262 0.00624 -0.0573 0.0304 1.0000
8.000 1.1412 0.01299 0.00661 -0.0565 0.0266 1.0000
8.250 1.1640 0.01331 0.00696 -0.0558 0.0248 1.0000
8.500 1.1860 0.01369 0.00734 -0.0549 0.0215 1.0000
8.750 1.2070 0.01413 0.00777 -0.0539 0.0177 1.0000
9.000 1.2278 0.01456 0.00821 -0.0529 0.0145 1.0000
9.250 1.2476 0.01507 0.00872 -0.0517 0.0111 1.0000
9.500 1.2666 0.01561 0.00927 -0.0504 0.0088 1.0000
9.750 1.2860 0.01611 0.00980 -0.0492 0.0076 1.0000
10.000 1.3048 0.01661 0.01035 -0.0479 0.0069 1.0000
10.250 1.3223 0.01719 0.01096 -0.0464 0.0062 1.0000
10.500 1.3382 0.01782 0.01164 -0.0446 0.0054 1.0000
10.750 1.3526 0.01841 0.01229 -0.0426 0.0050 1.0000
11.000 1.3671 0.01893 0.01288 -0.0406 0.0048 1.0000
11.250 1.3801 0.01955 0.01358 -0.0384 0.0046 1.0000
11.500 1.3933 0.02016 0.01425 -0.0364 0.0043 1.0000
11.750 1.4058 0.02084 0.01499 -0.0343 0.0040 1.0000
12.000 1.4172 0.02160 0.01582 -0.0322 0.0038 1.0000
12.250 1.4271 0.02247 0.01676 -0.0300 0.0036 1.0000
12.500 1.4361 0.02343 0.01779 -0.0279 0.0033 1.0000
12.750 1.4423 0.02463 0.01909 -0.0256 0.0031 1.0000
13.000 1.4491 0.02583 0.02038 -0.0236 0.0030 1.0000
13.250 1.4581 0.02690 0.02153 -0.0219 0.0029 1.0000
13.500 1.4656 0.02813 0.02285 -0.0203 0.0029 1.0000
13.750 1.4727 0.02945 0.02426 -0.0189 0.0027 1.0000
14.000 1.4768 0.03109 0.02603 -0.0173 0.0027 1.0000
14.250 1.4823 0.03267 0.02770 -0.0161 0.0026 1.0000
14.500 1.4866 0.03443 0.02956 -0.0150 0.0025 1.0000
14.750 1.4887 0.03648 0.03172 -0.0141 0.0024 1.0000
15.000 1.4911 0.03858 0.03392 -0.0133 0.0023 1.0000
15.250 1.4924 0.04089 0.03634 -0.0127 0.0023 1.0000
15.500 1.4924 0.04342 0.03897 -0.0123 0.0022 1.0000
15.750 1.4899 0.04635 0.04202 -0.0122 0.0021 1.0000
16.000 1.4858 0.04960 0.04539 -0.0123 0.0021 1.0000
16.250 1.4831 0.05280 0.04870 -0.0127 0.0020 1.0000
16.500 1.4763 0.05673 0.05276 -0.0134 0.0020 1.0000
16.750 1.4713 0.06059 0.05671 -0.0144 0.0019 1.0000
17.000 1.4602 0.06554 0.06182 -0.0160 0.0019 1.0000
17.250 1.4502 0.07061 0.06701 -0.0179 0.0019 1.0000
17.500 1.4368 0.07652 0.07305 -0.0204 0.0019 1.0000
17.750 1.4217 0.08301 0.07969 -0.0235 0.0018 1.0000
18.000 1.4064 0.08985 0.08667 -0.0269 0.0018 1.0000
18.250 1.3823 0.09871 0.09571 -0.0316 0.0019 1.0000
18.500 1.3615 0.10728 0.10442 -0.0362 0.0018 1.0000
18.750 1.3345 0.11748 0.11479 -0.0420 0.0018 1.0000
19.000 1.3084 0.12778 0.12524 -0.0479 0.0019 1.0000
19.250 1.2806 0.13879 0.13640 -0.0543 0.0019 1.0000
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Polar data table (+)
Polar graphs
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