XFOIL Version 6.94 Calculated polar for: WASP (smoothed) 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 0.4027 0.00618 0.00180 -0.0834 0.7168 1.0000 0.500 0.4521 0.00644 0.00176 -0.0816 0.6727 1.0000 1.000 0.5014 0.00672 0.00178 -0.0799 0.6280 1.0000 1.500 0.5503 0.00705 0.00185 -0.0781 0.5843 1.0000 2.000 0.5998 0.00738 0.00197 -0.0765 0.5429 1.0000 2.500 0.6494 0.00774 0.00214 -0.0749 0.5059 1.0000 3.000 0.6992 0.00810 0.00235 -0.0735 0.4717 1.0000 3.500 0.7492 0.00847 0.00260 -0.0721 0.4414 1.0000 4.000 0.7990 0.00887 0.00289 -0.0707 0.4111 1.0000 4.500 0.8488 0.00929 0.00322 -0.0693 0.3828 1.0000 5.000 0.8984 0.00972 0.00360 -0.0680 0.3535 1.0000 5.500 0.9475 0.01021 0.00403 -0.0665 0.3256 1.0000 6.000 0.9956 0.01078 0.00452 -0.0650 0.2959 1.0000 6.500 1.0431 0.01139 0.00505 -0.0634 0.2582 1.0000 7.000 1.0895 0.01210 0.00565 -0.0617 0.2216 1.0000 7.500 1.1353 0.01287 0.00636 -0.0599 0.1896 1.0000 8.000 1.1800 0.01373 0.00714 -0.0580 0.1578 1.0000 8.500 1.2217 0.01484 0.00811 -0.0558 0.1172 1.0000 9.000 1.2498 0.01720 0.00997 -0.0516 0.0427 1.0000 9.500 1.2800 0.01925 0.01206 -0.0475 0.0276 1.0000 10.000 1.3108 0.02101 0.01396 -0.0437 0.0226 1.0000 11.000 1.3460 0.02540 0.01879 -0.0325 0.0182 1.0000 11.500 1.3587 0.02777 0.02131 -0.0273 0.0165 1.0000 12.000 1.3526 0.03197 0.02572 -0.0217 0.0153 1.0000 12.500 1.3481 0.03686 0.03088 -0.0180 0.0146 1.0000 13.000 1.3526 0.04144 0.03574 -0.0163 0.0140 1.0000 13.500 1.3517 0.04706 0.04163 -0.0154 0.0134 1.0000 14.000 1.3470 0.05353 0.04836 -0.0154 0.0128 1.0000 14.500 1.3390 0.06080 0.05588 -0.0165 0.0123 1.0000 15.000 1.3281 0.06889 0.06421 -0.0186 0.0119 1.0000 15.500 1.3143 0.07779 0.07332 -0.0215 0.0114 1.0000 16.000 1.2962 0.08775 0.08350 -0.0250 0.0111 1.0000 16.500 1.2711 0.09919 0.09521 -0.0293 0.0108 1.0000 17.000 1.2398 0.11255 0.10887 -0.0352 0.0106 1.0000 17.500 1.2086 0.12690 0.12352 -0.0424 0.0106 1.0000 18.000 1.1794 0.14205 0.13894 -0.0509 0.0106 1.0000 18.500 1.1512 0.15804 0.15519 -0.0603 0.0107 1.0000 19.000 1.1194 0.17688 0.17431 -0.0717 0.0109 1.0000