XFOIL Version 6.96 Calculated polar for: HQ 2.5/12 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4130 0.09691 0.09463 -0.0433 1.0000 0.0236 -10.500 -0.5896 0.05034 0.04793 -0.0690 1.0000 0.0120 -10.250 -0.6196 0.04534 0.04281 -0.0708 1.0000 0.0118 -10.000 -0.6528 0.04324 0.04067 -0.0668 1.0000 0.0117 -9.750 -0.6799 0.03686 0.03384 -0.0675 0.9950 0.0115 -9.500 -0.6719 0.02984 0.02610 -0.0717 0.9869 0.0116 -9.250 -0.6471 0.02616 0.02194 -0.0745 0.9832 0.0119 -9.000 -0.6216 0.02363 0.01904 -0.0760 0.9780 0.0123 -8.750 -0.5920 0.02164 0.01675 -0.0777 0.9742 0.0126 -8.500 -0.5585 0.02041 0.01529 -0.0796 0.9714 0.0130 -8.250 -0.5321 0.01801 0.01267 -0.0808 0.9665 0.0141 -8.000 -0.5029 0.01719 0.01178 -0.0816 0.9604 0.0150 -7.750 -0.4719 0.01625 0.01072 -0.0827 0.9559 0.0160 -7.500 -0.4468 0.01545 0.00979 -0.0824 0.9475 0.0168 -7.250 -0.4200 0.01452 0.00872 -0.0825 0.9412 0.0181 -7.000 -0.3973 0.01376 0.00792 -0.0817 0.9320 0.0199 -6.750 -0.3707 0.01332 0.00742 -0.0815 0.9254 0.0221 -6.500 -0.3472 0.01273 0.00678 -0.0808 0.9168 0.0257 -6.250 -0.3204 0.01253 0.00655 -0.0806 0.9101 0.0302 -6.000 -0.2963 0.01200 0.00597 -0.0800 0.9020 0.0357 -5.750 -0.2694 0.01186 0.00576 -0.0798 0.8955 0.0402 -5.500 -0.2448 0.01140 0.00527 -0.0793 0.8876 0.0453 -5.250 -0.2181 0.01121 0.00503 -0.0791 0.8813 0.0499 -5.000 -0.1915 0.01106 0.00481 -0.0788 0.8739 0.0531 -4.750 -0.1661 0.01062 0.00434 -0.0784 0.8678 0.0601 -4.500 -0.1394 0.01045 0.00413 -0.0782 0.8605 0.0653 -4.250 -0.1134 0.01005 0.00371 -0.0779 0.8544 0.0740 -4.000 -0.0871 0.00975 0.00342 -0.0776 0.8474 0.0867 -3.750 -0.0608 0.00940 0.00313 -0.0774 0.8411 0.1122 -3.500 -0.0356 0.00887 0.00288 -0.0772 0.8345 0.1845 -3.250 -0.0104 0.00832 0.00264 -0.0770 0.8279 0.2783 -3.000 0.0138 0.00765 0.00244 -0.0768 0.8216 0.4196 -2.750 0.0395 0.00733 0.00238 -0.0764 0.8146 0.5077 -2.500 0.0665 0.00723 0.00235 -0.0761 0.8085 0.5551 -2.250 0.0938 0.00717 0.00232 -0.0759 0.8012 0.5841 -1.750 0.1490 0.00716 0.00230 -0.0755 0.7882 0.6298 -1.500 0.1770 0.00717 0.00227 -0.0754 0.7823 0.6450 -1.250 0.2047 0.00718 0.00228 -0.0752 0.7757 0.6602 -1.000 0.2320 0.00721 0.00229 -0.0749 0.7685 0.6794 -0.750 0.2593 0.00723 0.00231 -0.0746 0.7603 0.6937 -0.500 0.2869 0.00724 0.00228 -0.0744 0.7525 0.7037 -0.250 0.3143 0.00723 0.00228 -0.0742 0.7436 0.7127 0.000 0.3420 0.00727 0.00226 -0.0740 0.7355 0.7226 0.250 0.3693 0.00727 0.00227 -0.0737 0.7265 0.7321 0.500 0.3969 0.00728 0.00227 -0.0736 0.7190 0.7405 0.750 0.4246 0.00730 0.00227 -0.0735 0.7110 0.7477 1.000 0.4523 0.00731 0.00228 -0.0734 0.7028 0.7544 1.250 0.4797 0.00734 0.00229 -0.0732 0.6943 0.7616 1.500 0.5072 0.00735 0.00231 -0.0731 0.6848 0.7687 1.750 0.5345 0.00738 0.00234 -0.0729 0.6754 0.7762 2.000 0.5616 0.00741 0.00236 -0.0727 0.6655 0.7838 2.250 0.5887 0.00743 0.00240 -0.0725 0.6546 0.7920 2.500 0.6155 0.00746 0.00244 -0.0722 0.6433 0.8001 3.000 0.6683 0.00754 0.00255 -0.0715 0.6168 0.8184 3.250 0.6942 0.00759 0.00260 -0.0710 0.6004 0.8285 3.500 0.7197 0.00767 0.00268 -0.0705 0.5819 0.8399 3.750 0.7444 0.00776 0.00275 -0.0698 0.5613 0.8527 4.000 0.7684 0.00785 0.00285 -0.0690 0.5380 0.8681 4.250 0.7909 0.00796 0.00296 -0.0679 0.5111 0.8899 4.500 0.8149 0.00811 0.00311 -0.0670 0.4785 0.9327 4.750 0.8505 0.00846 0.00331 -0.0690 0.4390 1.0000 5.000 0.8731 0.00890 0.00356 -0.0683 0.3999 1.0000 5.250 0.8953 0.00935 0.00384 -0.0675 0.3621 1.0000 5.500 0.9179 0.00979 0.00412 -0.0668 0.3299 1.0000 5.750 0.9402 0.01023 0.00442 -0.0660 0.3026 1.0000 6.000 0.9632 0.01063 0.00473 -0.0654 0.2813 1.0000 6.250 0.9863 0.01100 0.00505 -0.0647 0.2648 1.0000 6.500 1.0095 0.01136 0.00536 -0.0640 0.2502 1.0000 6.750 1.0325 0.01172 0.00568 -0.0633 0.2355 1.0000 7.000 1.0549 0.01211 0.00601 -0.0626 0.2189 1.0000 7.250 1.0768 0.01252 0.00634 -0.0617 0.2011 1.0000 7.500 1.0988 0.01291 0.00670 -0.0609 0.1848 1.0000 7.750 1.1201 0.01334 0.00706 -0.0600 0.1679 1.0000 8.000 1.1405 0.01381 0.00746 -0.0590 0.1513 1.0000 8.250 1.1605 0.01429 0.00788 -0.0579 0.1367 1.0000 8.500 1.1800 0.01478 0.00833 -0.0567 0.1232 1.0000 8.750 1.1983 0.01533 0.00882 -0.0553 0.1088 1.0000 9.000 1.2157 0.01590 0.00933 -0.0539 0.0952 1.0000 9.250 1.2314 0.01647 0.00986 -0.0521 0.0824 1.0000 9.500 1.2457 0.01708 0.01041 -0.0501 0.0705 1.0000 9.750 1.2580 0.01781 0.01107 -0.0478 0.0570 1.0000 10.000 1.2633 0.01900 0.01205 -0.0447 0.0310 1.0000 10.250 1.2643 0.02050 0.01340 -0.0412 0.0136 1.0000 10.500 1.2730 0.02158 0.01451 -0.0388 0.0107 1.0000 10.750 1.2842 0.02250 0.01553 -0.0369 0.0096 1.0000 11.000 1.2940 0.02354 0.01665 -0.0349 0.0088 1.0000 11.250 1.3020 0.02474 0.01794 -0.0328 0.0083 1.0000 11.500 1.3058 0.02629 0.01961 -0.0305 0.0078 1.0000 11.750 1.3135 0.02759 0.02100 -0.0288 0.0076 1.0000 12.000 1.3203 0.02899 0.02250 -0.0271 0.0074 1.0000 12.250 1.3252 0.03059 0.02422 -0.0255 0.0073 1.0000 12.500 1.3287 0.03238 0.02612 -0.0239 0.0071 1.0000 12.750 1.3316 0.03429 0.02813 -0.0226 0.0069 1.0000 13.000 1.3328 0.03643 0.03039 -0.0213 0.0068 1.0000 13.250 1.3331 0.03875 0.03283 -0.0203 0.0066 1.0000 13.500 1.3324 0.04129 0.03547 -0.0195 0.0063 1.0000 13.750 1.3304 0.04405 0.03836 -0.0189 0.0063 1.0000 14.000 1.3273 0.04707 0.04148 -0.0185 0.0062 1.0000 14.250 1.3227 0.05041 0.04494 -0.0184 0.0061 1.0000 14.500 1.3185 0.05386 0.04851 -0.0186 0.0061 1.0000 14.750 1.3125 0.05773 0.05250 -0.0191 0.0060 1.0000 15.000 1.3068 0.06173 0.05663 -0.0199 0.0060 1.0000 15.250 1.2968 0.06654 0.06155 -0.0212 0.0059 1.0000 15.500 1.2913 0.07090 0.06605 -0.0225 0.0059 1.0000 15.750 1.2815 0.07608 0.07134 -0.0243 0.0058 1.0000 16.000 1.2772 0.08060 0.07600 -0.0260 0.0059 1.0000 16.250 1.2667 0.08622 0.08174 -0.0282 0.0058 1.0000 16.500 1.2612 0.09124 0.08689 -0.0304 0.0059 1.0000