XFOIL Version 6.94 Calculated polar for: HQ 3.0/11 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4090 0.00717 0.00233 -0.0885 0.7651 0.7319 0.500 0.4637 0.00713 0.00230 -0.0880 0.7496 0.7589 1.000 0.5177 0.00711 0.00232 -0.0874 0.7330 0.7924 1.500 0.5694 0.00711 0.00240 -0.0862 0.7129 0.8386 2.000 0.6195 0.00708 0.00241 -0.0846 0.6914 0.8872 2.500 0.6757 0.00699 0.00243 -0.0842 0.6686 0.9575 3.000 0.7386 0.00713 0.00251 -0.0859 0.6406 1.0000 3.500 0.7909 0.00739 0.00266 -0.0853 0.6056 1.0000 4.000 0.8349 0.00802 0.00285 -0.0830 0.5144 1.0000 4.500 0.8773 0.00890 0.00329 -0.0808 0.4238 1.0000 5.000 0.9126 0.01033 0.00400 -0.0775 0.2940 1.0000 5.500 0.9566 0.01121 0.00462 -0.0758 0.2410 1.0000 6.000 0.9961 0.01237 0.00536 -0.0734 0.1671 1.0000 6.500 1.0360 0.01345 0.00616 -0.0710 0.1147 1.0000 7.000 1.0686 0.01497 0.00726 -0.0676 0.0516 1.0000 7.500 1.0988 0.01654 0.00858 -0.0637 0.0114 1.0000 8.000 1.1297 0.01771 0.00981 -0.0596 0.0031 1.0000 8.500 1.1609 0.01875 0.01098 -0.0557 0.0028 1.0000 9.000 1.1899 0.01996 0.01235 -0.0516 0.0027 1.0000 9.500 1.2162 0.02139 0.01397 -0.0475 0.0027 1.0000 10.000 1.2394 0.02308 0.01585 -0.0433 0.0027 1.0000 10.500 1.2588 0.02512 0.01811 -0.0391 0.0027 1.0000 11.000 1.2739 0.02758 0.02078 -0.0349 0.0028 1.0000 11.500 1.2833 0.03061 0.02403 -0.0309 0.0028 1.0000 12.000 1.2865 0.03438 0.02804 -0.0272 0.0029 1.0000 12.500 1.2859 0.03885 0.03275 -0.0242 0.0029 1.0000 13.000 1.2804 0.04429 0.03844 -0.0222 0.0030 1.0000 13.500 1.2725 0.05061 0.04503 -0.0213 0.0031 1.0000 14.000 1.2630 0.05783 0.05251 -0.0216 0.0032 1.0000 14.500 1.2518 0.06603 0.06099 -0.0231 0.0033 1.0000 15.000 1.2395 0.07520 0.07044 -0.0259 0.0034 1.0000 15.500 1.2245 0.08558 0.08110 -0.0298 0.0035 1.0000 16.000 1.2082 0.09695 0.09276 -0.0349 0.0035 1.0000 16.500 1.1900 0.10934 0.10544 -0.0411 0.0036 1.0000 17.000 1.1752 0.12158 0.11794 -0.0478 0.0037 1.0000 17.500 1.1616 0.13444 0.13106 -0.0557 0.0037 1.0000 18.000 1.1453 0.14840 0.14529 -0.0646 0.0038 1.0000 18.500 1.1256 0.16382 0.16101 -0.0744 0.0039 1.0000 19.000 1.1012 0.18137 0.17885 -0.0855 0.0040 1.0000 19.500 1.0657 0.20414 0.20189 -0.0988 0.0041 1.0000