XFOIL Version 6.94 Calculated polar for: SD7003-085-88 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 0.1764 0.00578 0.00165 -0.0348 0.7402 0.8888 0.500 0.2284 0.00588 0.00160 -0.0328 0.6838 0.9535 1.000 0.3066 0.00610 0.00153 -0.0372 0.6226 0.9993 1.500 0.3572 0.00641 0.00157 -0.0361 0.5665 1.0000 2.000 0.4094 0.00677 0.00166 -0.0352 0.5113 1.0000 2.500 0.4624 0.00716 0.00181 -0.0345 0.4582 1.0000 3.500 0.5694 0.00804 0.00228 -0.0334 0.3564 1.0000 4.000 0.6230 0.00853 0.00259 -0.0329 0.3089 1.0000 4.500 0.6764 0.00906 0.00299 -0.0324 0.2652 1.0000 5.000 0.7293 0.00968 0.00343 -0.0319 0.2231 1.0000 5.500 0.7822 0.01030 0.00396 -0.0313 0.1875 1.0000 6.000 0.8346 0.01099 0.00457 -0.0307 0.1557 1.0000 6.500 0.8863 0.01176 0.00525 -0.0301 0.1256 1.0000 7.000 0.9377 0.01255 0.00598 -0.0294 0.0997 1.0000 7.500 0.9884 0.01342 0.00684 -0.0287 0.0786 1.0000 8.000 1.0382 0.01439 0.00782 -0.0278 0.0600 1.0000 8.500 1.0851 0.01575 0.00917 -0.0266 0.0412 1.0000 9.000 1.1295 0.01741 0.01093 -0.0250 0.0293 1.0000 9.500 1.1674 0.01978 0.01344 -0.0227 0.0236 1.0000 10.000 1.2086 0.02152 0.01543 -0.0208 0.0216 1.0000 10.500 1.2455 0.02356 0.01768 -0.0186 0.0196 1.0000 11.000 1.2697 0.02679 0.02114 -0.0153 0.0176 1.0000 11.500 1.2876 0.03034 0.02506 -0.0115 0.0167 1.0000 12.000 1.2991 0.03308 0.02809 -0.0070 0.0158 1.0000 12.500 1.3001 0.03659 0.03188 -0.0031 0.0148 1.0000 13.000 1.2960 0.04134 0.03689 -0.0018 0.0141 1.0000 13.500 1.2858 0.04803 0.04384 -0.0033 0.0135 1.0000 14.000 1.2673 0.05727 0.05337 -0.0075 0.0132 1.0000 14.500 1.2416 0.06893 0.06535 -0.0141 0.0131 1.0000 15.000 1.2096 0.08281 0.07952 -0.0225 0.0128 1.0000 15.500 1.1720 0.09920 0.09624 -0.0327 0.0130 1.0000 16.000 1.1198 0.12098 0.11840 -0.0465 0.0134 1.0000