S4053 (s4053-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 500,000 Max Cl/Cd: 96.46 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4053-il-500000-n5.txt Download as CSV file: xf-s4053-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3164 0.07571 0.07361 -0.0356 1.0000 0.0105
-8.250 -0.3997 0.08065 0.07846 -0.0342 1.0000 0.0105
-8.000 -0.4077 0.07735 0.07521 -0.0344 1.0000 0.0099
-7.750 -0.4164 0.07364 0.07154 -0.0358 0.9988 0.0096
-7.500 -0.4010 0.06536 0.06325 -0.0481 0.9903 0.0092
-7.250 -0.3849 0.05423 0.05198 -0.0620 0.9803 0.0086
-6.750 -0.3492 0.03809 0.03528 -0.0744 0.9583 0.0088
-6.500 -0.3301 0.03087 0.02758 -0.0771 0.9458 0.0088
-6.250 -0.3068 0.02580 0.02201 -0.0786 0.9336 0.0090
-6.000 -0.2799 0.02314 0.01900 -0.0796 0.9212 0.0094
-5.750 -0.2537 0.02094 0.01643 -0.0800 0.9070 0.0099
-5.500 -0.2294 0.01870 0.01377 -0.0796 0.8915 0.0099
-5.250 -0.2054 0.01686 0.01153 -0.0790 0.8765 0.0099
-5.000 -0.1810 0.01542 0.00977 -0.0783 0.8622 0.0098
-4.750 -0.1563 0.01427 0.00837 -0.0776 0.8487 0.0100
-4.500 -0.1313 0.01334 0.00723 -0.0769 0.8361 0.0101
-4.250 -0.1061 0.01256 0.00628 -0.0763 0.8242 0.0104
-4.000 -0.0808 0.01193 0.00550 -0.0757 0.8131 0.0108
-3.750 -0.0553 0.01142 0.00485 -0.0752 0.8025 0.0112
-3.500 -0.0295 0.01100 0.00433 -0.0747 0.7921 0.0116
-3.250 -0.0034 0.01067 0.00392 -0.0743 0.7824 0.0119
-3.000 0.0218 0.01014 0.00328 -0.0737 0.7732 0.0124
-2.750 0.0477 0.00977 0.00283 -0.0733 0.7640 0.0136
-2.500 0.0742 0.00954 0.00255 -0.0730 0.7555 0.0148
-2.000 0.1277 0.00917 0.00201 -0.0724 0.7388 0.0161
-1.750 0.1546 0.00904 0.00179 -0.0721 0.7311 0.0174
-1.500 0.1815 0.00888 0.00160 -0.0718 0.7230 0.0241
-1.250 0.2072 0.00848 0.00147 -0.0715 0.7155 0.1067
-1.000 0.2325 0.00806 0.00138 -0.0712 0.7077 0.2197
-0.750 0.2570 0.00753 0.00134 -0.0709 0.7003 0.3833
-0.500 0.2799 0.00696 0.00135 -0.0701 0.6926 0.5733
-0.250 0.3042 0.00668 0.00136 -0.0693 0.6848 0.6716
0.250 0.3582 0.00611 0.00146 -0.0682 0.6682 0.9276
0.500 0.4081 0.00615 0.00145 -0.0729 0.6585 0.9786
1.000 0.4828 0.00627 0.00142 -0.0771 0.6389 0.9985
1.250 0.5107 0.00633 0.00143 -0.0772 0.6290 1.0000
1.500 0.5353 0.00642 0.00146 -0.0765 0.6182 1.0000
1.750 0.5598 0.00651 0.00149 -0.0757 0.6061 1.0000
2.000 0.5844 0.00660 0.00154 -0.0750 0.5930 1.0000
2.250 0.6090 0.00671 0.00159 -0.0743 0.5791 1.0000
2.500 0.6334 0.00682 0.00165 -0.0736 0.5644 1.0000
2.750 0.6578 0.00695 0.00173 -0.0729 0.5473 1.0000
3.000 0.6817 0.00711 0.00181 -0.0720 0.5262 1.0000
3.250 0.7051 0.00731 0.00191 -0.0711 0.5002 1.0000
3.500 0.7281 0.00755 0.00204 -0.0702 0.4709 1.0000
3.750 0.7507 0.00785 0.00221 -0.0692 0.4387 1.0000
4.000 0.7733 0.00816 0.00239 -0.0682 0.4045 1.0000
4.250 0.7954 0.00853 0.00260 -0.0672 0.3679 1.0000
4.500 0.8173 0.00894 0.00284 -0.0662 0.3291 1.0000
4.750 0.8387 0.00941 0.00311 -0.0651 0.2871 1.0000
5.000 0.8599 0.00990 0.00343 -0.0641 0.2454 1.0000
5.250 0.8819 0.01034 0.00373 -0.0631 0.2130 1.0000
5.500 0.9043 0.01075 0.00403 -0.0623 0.1864 1.0000
5.750 0.9264 0.01117 0.00435 -0.0614 0.1619 1.0000
6.000 0.9484 0.01162 0.00469 -0.0605 0.1371 1.0000
6.250 0.9701 0.01208 0.00506 -0.0595 0.1145 1.0000
6.500 0.9920 0.01252 0.00545 -0.0586 0.0973 1.0000
6.750 1.0139 0.01295 0.00584 -0.0577 0.0837 1.0000
7.000 1.0360 0.01337 0.00623 -0.0568 0.0727 1.0000
7.250 1.0577 0.01380 0.00664 -0.0559 0.0623 1.0000
7.500 1.0790 0.01426 0.00708 -0.0549 0.0531 1.0000
7.750 1.0998 0.01475 0.00756 -0.0539 0.0448 1.0000
8.000 1.1207 0.01521 0.00802 -0.0529 0.0388 1.0000
8.250 1.1414 0.01568 0.00851 -0.0518 0.0343 1.0000
8.500 1.1622 0.01612 0.00899 -0.0508 0.0310 1.0000
8.750 1.1816 0.01666 0.00954 -0.0496 0.0272 1.0000
9.000 1.2014 0.01714 0.01008 -0.0484 0.0247 1.0000
9.250 1.2206 0.01764 0.01063 -0.0472 0.0214 1.0000
9.500 1.2377 0.01828 0.01129 -0.0457 0.0176 1.0000
9.750 1.2550 0.01886 0.01192 -0.0442 0.0149 1.0000
10.000 1.2689 0.01959 0.01265 -0.0422 0.0120 1.0000
10.250 1.2827 0.02023 0.01338 -0.0401 0.0107 1.0000
10.500 1.2949 0.02097 0.01417 -0.0378 0.0095 1.0000
10.750 1.3060 0.02181 0.01507 -0.0355 0.0087 1.0000
11.000 1.3149 0.02281 0.01617 -0.0330 0.0079 1.0000
11.250 1.3258 0.02368 0.01713 -0.0309 0.0075 1.0000
11.500 1.3361 0.02460 0.01816 -0.0289 0.0071 1.0000
11.750 1.3453 0.02564 0.01932 -0.0269 0.0066 1.0000
12.000 1.3543 0.02671 0.02048 -0.0250 0.0062 1.0000
12.250 1.3606 0.02804 0.02191 -0.0231 0.0058 1.0000
12.500 1.3651 0.02957 0.02355 -0.0212 0.0056 1.0000
12.750 1.3657 0.03150 0.02561 -0.0192 0.0052 1.0000
13.000 1.3654 0.03361 0.02786 -0.0175 0.0051 1.0000
13.250 1.3707 0.03532 0.02969 -0.0164 0.0049 1.0000
13.500 1.3733 0.03735 0.03185 -0.0153 0.0048 1.0000
13.750 1.3745 0.03961 0.03426 -0.0144 0.0047 1.0000
14.000 1.3736 0.04221 0.03699 -0.0138 0.0046 1.0000
14.250 1.3724 0.04492 0.03985 -0.0134 0.0045 1.0000
14.500 1.3712 0.04778 0.04285 -0.0132 0.0043 1.0000
14.750 1.3682 0.05096 0.04617 -0.0133 0.0041 1.0000
15.000 1.3630 0.05456 0.04991 -0.0137 0.0040 1.0000
15.250 1.3596 0.05810 0.05360 -0.0144 0.0039 1.0000
15.500 1.3538 0.06214 0.05778 -0.0155 0.0038 1.0000
15.750 1.3449 0.06685 0.06265 -0.0170 0.0037 1.0000
16.000 1.3324 0.07242 0.06838 -0.0192 0.0037 1.0000
16.250 1.3233 0.07773 0.07383 -0.0215 0.0036 1.0000
16.500 1.3083 0.08435 0.08062 -0.0246 0.0036 1.0000
16.750 1.2972 0.09061 0.08701 -0.0278 0.0035 1.0000
17.000 1.2805 0.09815 0.09472 -0.0317 0.0036 1.0000
17.250 1.2626 0.10626 0.10298 -0.0361 0.0036 1.0000
17.500 1.2435 0.11494 0.11182 -0.0409 0.0036 1.0000
17.750 1.2240 0.12391 0.12094 -0.0459 0.0036 1.0000
18.000 1.2069 0.13263 0.12978 -0.0509 0.0036 1.0000
18.250 1.1847 0.14277 0.14007 -0.0567 0.0037 1.0000
18.500 1.1667 0.15215 0.14956 -0.0622 0.0037 1.0000
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