XFOIL Version 6.96 Calculated polar for: NACA 65(4)-421 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9796 0.07928 0.07559 -0.0811 1.0000 0.0216 -19.500 -0.9829 0.07578 0.07199 -0.0824 1.0000 0.0217 -19.250 -0.9830 0.07262 0.06877 -0.0838 1.0000 0.0219 -19.000 -0.9835 0.06958 0.06563 -0.0848 1.0000 0.0220 -18.750 -0.9829 0.06665 0.06262 -0.0859 1.0000 0.0223 -18.500 -0.9818 0.06391 0.05979 -0.0867 1.0000 0.0224 -18.250 -0.9798 0.06131 0.05710 -0.0874 1.0000 0.0226 -18.000 -0.9770 0.05884 0.05455 -0.0881 1.0000 0.0227 -17.750 -0.9736 0.05650 0.05213 -0.0886 1.0000 0.0228 -17.500 -0.9687 0.05439 0.04994 -0.0890 1.0000 0.0229 -17.250 -0.9646 0.05220 0.04768 -0.0895 1.0000 0.0230 -17.000 -0.9578 0.05050 0.04590 -0.0889 1.0000 0.0233 -16.750 -0.9487 0.04905 0.04445 -0.0885 1.0000 0.0237 -16.500 -0.9410 0.04743 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0.00256 -0.0702 0.6357 0.5907 -2.250 0.0722 0.00756 0.00253 -0.0707 0.6331 0.5939 -2.000 0.1017 0.00757 0.00253 -0.0712 0.6307 0.5965 -1.750 0.1313 0.00755 0.00252 -0.0718 0.6291 0.5985 -1.500 0.1610 0.00754 0.00251 -0.0723 0.6272 0.6005 -1.250 0.1906 0.00754 0.00250 -0.0729 0.6251 0.6024 -1.000 0.2203 0.00755 0.00250 -0.0734 0.6229 0.6045 -0.750 0.2498 0.00757 0.00249 -0.0740 0.6208 0.6065 -0.500 0.2794 0.00760 0.00250 -0.0745 0.6187 0.6082 -0.250 0.3089 0.00766 0.00251 -0.0751 0.6165 0.6096 0.000 0.3385 0.00770 0.00253 -0.0757 0.6138 0.6118 0.250 0.3678 0.00768 0.00254 -0.0762 0.6124 0.6143 0.500 0.3972 0.00767 0.00257 -0.0767 0.6107 0.6166 0.750 0.4265 0.00768 0.00259 -0.0772 0.6088 0.6187 1.000 0.4559 0.00770 0.00262 -0.0777 0.6068 0.6207 1.250 0.4853 0.00773 0.00265 -0.0783 0.6049 0.6227 1.500 0.5147 0.00776 0.00269 -0.0788 0.6031 0.6247 1.750 0.5440 0.00781 0.00273 -0.0793 0.6011 0.6265 2.000 0.5734 0.00788 0.00278 -0.0798 0.5989 0.6281 2.250 0.6029 0.00797 0.00286 -0.0804 0.5961 0.6307 2.500 0.6318 0.00796 0.00291 -0.0809 0.5947 0.6335 2.750 0.6607 0.00798 0.00297 -0.0813 0.5932 0.6359 3.000 0.6896 0.00800 0.00304 -0.0818 0.5913 0.6382 3.250 0.7184 0.00803 0.00309 -0.0822 0.5891 0.6405 3.500 0.7470 0.00806 0.00314 -0.0826 0.5864 0.6428 3.750 0.7755 0.00811 0.00319 -0.0829 0.5835 0.6449 4.000 0.8041 0.00821 0.00327 -0.0834 0.5797 0.6468 4.250 0.8318 0.00822 0.00332 -0.0836 0.5765 0.6494 4.500 0.8585 0.00817 0.00334 -0.0836 0.5712 0.6525 4.750 0.8845 0.00819 0.00335 -0.0834 0.5644 0.6554 5.000 0.9114 0.00825 0.00344 -0.0835 0.5595 0.6583 5.250 0.9383 0.00826 0.00351 -0.0835 0.5543 0.6610 5.500 0.9628 0.00834 0.00356 -0.0831 0.5461 0.6636 5.750 0.9887 0.00839 0.00364 -0.0829 0.5377 0.6658 6.000 1.0117 0.00849 0.00373 -0.0823 0.5286 0.6692 6.250 1.0369 0.00854 0.00384 -0.0820 0.5199 0.6725 6.500 1.0586 0.00868 0.00398 -0.0811 0.5091 0.6758 6.750 1.0781 0.00887 0.00414 -0.0798 0.4944 0.6790 7.000 1.0927 0.00911 0.00433 -0.0776 0.4740 0.6823 7.250 1.0963 0.00954 0.00465 -0.0733 0.4460 0.6852 7.500 1.0937 0.01024 0.00521 -0.0681 0.4093 0.6898 7.750 1.0849 0.01125 0.00604 -0.0623 0.3685 0.6940 8.000 1.0764 0.01241 0.00704 -0.0569 0.3315 0.6983 8.250 1.0682 0.01372 0.00817 -0.0520 0.2950 0.7022 8.500 1.0600 0.01517 0.00945 -0.0474 0.2591 0.7059 8.750 1.0527 0.01670 0.01085 -0.0433 0.2261 0.7110 9.000 1.0505 0.01813 0.01218 -0.0401 0.2001 0.7157 9.250 1.0456 0.01980 0.01372 -0.0367 0.1706 0.7204 9.500 1.0434 0.02144 0.01523 -0.0339 0.1455 0.7244 9.750 1.0401 0.02317 0.01687 -0.0311 0.1202 0.7301 10.000 1.0379 0.02495 0.01854 -0.0287 0.0969 0.7356 10.250 1.0346 0.02690 0.02037 -0.0263 0.0726 0.7408 10.500 1.0331 0.02881 0.02217 -0.0242 0.0519 0.7459 10.750 1.0358 0.03050 0.02381 -0.0225 0.0387 0.7517 11.000 1.0431 0.03195 0.02527 -0.0213 0.0334 0.7575 11.250 1.0516 0.03336 0.02667 -0.0203 0.0302 0.7628 11.500 1.0626 0.03458 0.02795 -0.0195 0.0284 0.7693 11.750 1.0713 0.03601 0.02941 -0.0186 0.0266 0.7759 12.000 1.0825 0.03730 0.03074 -0.0180 0.0255 0.7821 12.250 1.0936 0.03859 0.03210 -0.0173 0.0247 0.7895 12.500 1.1042 0.03995 0.03351 -0.0167 0.0237 0.7971 12.750 1.1122 0.04155 0.03515 -0.0159 0.0227 0.8046 13.000 1.1206 0.04313 0.03681 -0.0153 0.0221 0.8128 13.250 1.1325 0.04446 0.03819 -0.0149 0.0216 0.8208 13.500 1.1424 0.04594 0.03975 -0.0143 0.0210 0.8298 13.750 1.1526 0.04746 0.04133 -0.0139 0.0206 0.8388 14.000 1.1619 0.04900 0.04295 -0.0134 0.0201 0.8490 14.250 1.1692 0.05078 0.04479 -0.0129 0.0196 0.8600 14.500 1.1709 0.05309 0.04719 -0.0122 0.0189 0.8728 14.750 1.1777 0.05486 0.04906 -0.0116 0.0188 0.8894 15.000 1.1846 0.05646 0.05080 -0.0108 0.0186 0.9149 15.250 1.1994 0.05821 0.05271 -0.0118 0.0183 0.9631 15.500 1.2073 0.06016 0.05471 -0.0119 0.0181 1.0000 15.750 1.2156 0.06217 0.05676 -0.0120 0.0178 1.0000 16.000 1.2236 0.06423 0.05886 -0.0121 0.0175 1.0000 16.250 1.2298 0.06653 0.06121 -0.0123 0.0173 1.0000 16.500 1.2377 0.06867 0.06339 -0.0125 0.0170 1.0000 16.750 1.2440 0.07101 0.06577 -0.0128 0.0168 1.0000 17.000 1.2490 0.07353 0.06834 -0.0132 0.0167 1.0000 17.250 1.2532 0.07616 0.07101 -0.0135 0.0164 1.0000 17.500 1.2547 0.07918 0.07408 -0.0140 0.0162 1.0000 17.750 1.2512 0.08281 0.07777 -0.0145 0.0158 1.0000 18.000 1.2552 0.08563 0.08065 -0.0151 0.0158 1.0000