XFOIL Version 6.96 Calculated polar for: S9037 (9%) 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3607 0.10120 0.09953 -0.0284 1.0000 0.0040 -9.500 -0.3587 0.09739 0.09574 -0.0297 1.0000 0.0041 -9.250 -0.3593 0.09334 0.09172 -0.0312 1.0000 0.0046 -9.000 -0.3552 0.09071 0.08910 -0.0320 1.0000 0.0047 -8.750 -0.3547 0.08721 0.08563 -0.0331 1.0000 0.0048 -8.250 -0.3405 0.08092 0.07937 -0.0374 0.9872 0.0051 -8.000 -0.3234 0.07579 0.07424 -0.0443 0.9784 0.0052 -7.750 -0.3031 0.07043 0.06886 -0.0526 0.9654 0.0055 -7.500 -0.2920 0.06339 0.06176 -0.0627 0.9396 0.0051 -7.250 -0.2948 0.05550 0.05375 -0.0706 0.9136 0.0048 -7.000 -0.2870 0.05052 0.04866 -0.0748 0.8985 0.0049 -6.750 -0.2755 0.04600 0.04402 -0.0780 0.8861 0.0052 -6.250 -0.2729 0.02078 0.01739 -0.0832 0.8610 0.0042 -6.000 -0.2535 0.01725 0.01332 -0.0827 0.8523 0.0041 -5.750 -0.2304 0.01525 0.01093 -0.0823 0.8434 0.0041 -5.500 -0.2057 0.01375 0.00913 -0.0819 0.8338 0.0041 -5.250 -0.1803 0.01262 0.00775 -0.0815 0.8243 0.0040 -5.000 -0.1544 0.01168 0.00659 -0.0811 0.8143 0.0040 -4.750 -0.1280 0.01091 0.00565 -0.0808 0.8045 0.0040 -4.500 -0.1013 0.01029 0.00487 -0.0806 0.7951 0.0040 -4.250 -0.0745 0.00978 0.00424 -0.0803 0.7851 0.0041 -4.000 -0.0475 0.00934 0.00368 -0.0801 0.7742 0.0041 -3.750 -0.0203 0.00896 0.00320 -0.0799 0.7629 0.0041 -3.500 0.0070 0.00865 0.00279 -0.0797 0.7511 0.0042 -3.250 0.0345 0.00840 0.00244 -0.0795 0.7391 0.0043 -3.000 0.0620 0.00821 0.00215 -0.0793 0.7272 0.0043 -2.500 0.1172 0.00782 0.00161 -0.0790 0.7037 0.0056 -2.250 0.1450 0.00770 0.00143 -0.0789 0.6922 0.0078 -2.000 0.1726 0.00756 0.00129 -0.0788 0.6807 0.0173 -1.750 0.2002 0.00744 0.00119 -0.0787 0.6679 0.0313 -1.500 0.2276 0.00731 0.00110 -0.0786 0.6538 0.0589 -1.000 0.2820 0.00693 0.00097 -0.0785 0.6243 0.1742 -0.500 0.3368 0.00671 0.00092 -0.0784 0.5957 0.2792 -0.250 0.3641 0.00663 0.00091 -0.0784 0.5815 0.3289 0.000 0.3914 0.00652 0.00092 -0.0783 0.5676 0.3921 0.250 0.4184 0.00638 0.00094 -0.0783 0.5527 0.4740 0.500 0.4453 0.00626 0.00097 -0.0782 0.5371 0.5566 0.750 0.4716 0.00614 0.00102 -0.0779 0.5185 0.6496 1.000 0.4970 0.00599 0.00109 -0.0775 0.4989 0.7532 1.250 0.5205 0.00584 0.00117 -0.0764 0.4814 0.8567 1.500 0.5435 0.00576 0.00124 -0.0750 0.4652 0.9541 1.750 0.5815 0.00587 0.00127 -0.0773 0.4490 0.9957 2.000 0.6096 0.00601 0.00133 -0.0774 0.4330 1.0000 2.250 0.6361 0.00618 0.00141 -0.0771 0.4145 1.0000 2.500 0.6625 0.00637 0.00149 -0.0769 0.3940 1.0000 2.750 0.6888 0.00657 0.00159 -0.0766 0.3743 1.0000 3.000 0.7154 0.00674 0.00168 -0.0764 0.3584 1.0000 3.250 0.7421 0.00691 0.00180 -0.0762 0.3440 1.0000 3.500 0.7686 0.00709 0.00191 -0.0760 0.3284 1.0000 3.750 0.7950 0.00729 0.00203 -0.0758 0.3126 1.0000 4.000 0.8215 0.00747 0.00216 -0.0756 0.2991 1.0000 4.250 0.8477 0.00770 0.00232 -0.0753 0.2817 1.0000 4.500 0.8732 0.00799 0.00250 -0.0750 0.2590 1.0000 4.750 0.8989 0.00825 0.00268 -0.0747 0.2400 1.0000 5.000 0.9248 0.00848 0.00287 -0.0745 0.2260 1.0000 5.250 0.9506 0.00873 0.00306 -0.0742 0.2113 1.0000 5.500 0.9758 0.00904 0.00328 -0.0738 0.1935 1.0000 5.750 1.0012 0.00931 0.00350 -0.0735 0.1796 1.0000 6.000 1.0267 0.00957 0.00373 -0.0732 0.1679 1.0000 6.250 1.0514 0.00992 0.00400 -0.0728 0.1516 1.0000 6.500 1.0757 0.01029 0.00429 -0.0723 0.1328 1.0000 6.750 1.1001 0.01064 0.00458 -0.0719 0.1183 1.0000 7.000 1.1244 0.01099 0.00489 -0.0714 0.1060 1.0000 7.250 1.1484 0.01137 0.00522 -0.0709 0.0935 1.0000 7.500 1.1715 0.01182 0.00559 -0.0703 0.0784 1.0000 7.750 1.1945 0.01226 0.00597 -0.0697 0.0660 1.0000 8.000 1.2179 0.01266 0.00634 -0.0691 0.0575 1.0000 8.250 1.2407 0.01309 0.00676 -0.0685 0.0495 1.0000 8.500 1.2626 0.01360 0.00722 -0.0677 0.0393 1.0000 8.750 1.2839 0.01413 0.00770 -0.0669 0.0303 1.0000 9.000 1.3056 0.01462 0.00817 -0.0660 0.0250 1.0000 9.250 1.3268 0.01512 0.00867 -0.0652 0.0201 1.0000 9.500 1.3468 0.01570 0.00923 -0.0642 0.0151 1.0000 9.750 1.3664 0.01628 0.00983 -0.0631 0.0112 1.0000 10.000 1.3843 0.01697 0.01050 -0.0618 0.0066 1.0000 10.250 1.4017 0.01767 0.01122 -0.0604 0.0040 1.0000 10.500 1.4188 0.01833 0.01192 -0.0589 0.0029 1.0000 10.750 1.4360 0.01893 0.01257 -0.0575 0.0026 1.0000 11.000 1.4506 0.01954 0.01324 -0.0556 0.0023 1.0000 11.250 1.4625 0.02023 0.01400 -0.0533 0.0021 1.0000 11.500 1.4742 0.02094 0.01478 -0.0511 0.0020 1.0000 11.750 1.4845 0.02176 0.01569 -0.0488 0.0018 1.0000 12.000 1.4940 0.02266 0.01667 -0.0466 0.0017 1.0000 12.250 1.5036 0.02358 0.01768 -0.0445 0.0016 1.0000 12.500 1.5128 0.02457 0.01874 -0.0425 0.0016 1.0000 12.750 1.5208 0.02567 0.01994 -0.0406 0.0016 1.0000 13.000 1.5280 0.02689 0.02125 -0.0387 0.0015 1.0000 13.250 1.5346 0.02821 0.02266 -0.0370 0.0015 1.0000 13.500 1.5395 0.02973 0.02428 -0.0354 0.0014 1.0000 13.750 1.5433 0.03142 0.02607 -0.0338 0.0013 1.0000 14.000 1.5468 0.03323 0.02798 -0.0325 0.0013 1.0000 14.250 1.5478 0.03536 0.03023 -0.0314 0.0013 1.0000 14.500 1.5488 0.03761 0.03260 -0.0305 0.0013 1.0000 14.750 1.5480 0.04019 0.03529 -0.0298 0.0012 1.0000 15.000 1.5456 0.04306 0.03829 -0.0294 0.0012 1.0000 15.250 1.5438 0.04603 0.04136 -0.0294 0.0012 1.0000 15.500 1.5388 0.04955 0.04501 -0.0296 0.0011 1.0000 15.750 1.5326 0.05341 0.04900 -0.0303 0.0011 1.0000 16.000 1.5238 0.05789 0.05361 -0.0314 0.0011 1.0000 16.250 1.5161 0.06242 0.05827 -0.0327 0.0011 1.0000 16.500 1.5064 0.06751 0.06348 -0.0346 0.0010 1.0000 16.750 1.4931 0.07344 0.06956 -0.0370 0.0010 1.0000 17.000 1.4776 0.08001 0.07628 -0.0399 0.0010 1.0000 17.250 1.4613 0.08700 0.08342 -0.0432 0.0010 1.0000 17.500 1.4480 0.09368 0.09022 -0.0465 0.0010 1.0000 17.750 1.4257 0.10231 0.09901 -0.0509 0.0010 1.0000 18.000 1.4064 0.11061 0.10745 -0.0553 0.0010 1.0000