XFOIL Version 6.94 Calculated polar for: FX 38-153 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 0.2006 0.01424 0.01003 -0.0520 0.8457 0.7998 0.500 0.2707 0.01391 0.00968 -0.0540 0.8427 0.8109 1.500 0.3795 0.01293 0.00870 -0.0523 0.8242 0.8185 2.500 0.4892 0.01208 0.00781 -0.0529 0.7879 0.8284 3.000 0.5535 0.01150 0.00719 -0.0545 0.7616 0.8314 3.500 0.6077 0.01130 0.00683 -0.0542 0.7139 0.8337 4.000 0.6441 0.01160 0.00681 -0.0505 0.6416 0.8366 4.500 0.6643 0.01232 0.00715 -0.0442 0.5607 0.8406 5.000 0.6888 0.01318 0.00765 -0.0393 0.4815 0.8453 5.500 0.7229 0.01405 0.00821 -0.0367 0.4137 0.8485 6.000 0.7572 0.01471 0.00866 -0.0338 0.3554 0.8515 6.500 0.7882 0.01550 0.00924 -0.0303 0.2986 0.8542 7.000 0.8201 0.01650 0.00996 -0.0273 0.2359 0.8567 7.500 0.8527 0.01767 0.01079 -0.0247 0.1721 0.8595 8.000 0.8903 0.01862 0.01161 -0.0229 0.1370 0.8626 8.500 0.9273 0.01978 0.01257 -0.0214 0.0977 0.8651 9.000 0.9618 0.02120 0.01375 -0.0197 0.0588 0.8673 10.000 1.0301 0.02392 0.01640 -0.0162 0.0253 0.8713 10.500 1.0592 0.02536 0.01785 -0.0137 0.0148 0.8736 11.000 1.0879 0.02690 0.01950 -0.0113 0.0132 0.8759 11.500 1.1156 0.02858 0.02133 -0.0089 0.0122 0.8786 12.000 1.1427 0.03040 0.02333 -0.0069 0.0111 0.8815 12.500 1.1639 0.03286 0.02595 -0.0047 0.0099 0.8839 13.000 1.1923 0.03488 0.02815 -0.0035 0.0090 0.8863 13.500 1.2166 0.03735 0.03079 -0.0022 0.0081 0.8884 14.000 1.2387 0.04009 0.03371 -0.0011 0.0072 0.8904 14.500 1.2588 0.04282 0.03669 0.0002 0.0048 0.8932 15.000 1.2700 0.04642 0.04040 0.0016 0.0028 0.8965 15.500 1.2765 0.05093 0.04510 0.0025 0.0023 0.8996 16.000 1.2792 0.05633 0.05074 0.0026 0.0022 0.9023 16.500 1.2780 0.06275 0.05743 0.0016 0.0021 0.9049 17.000 1.2720 0.07037 0.06533 -0.0005 0.0020 0.9071 17.500 1.2611 0.07934 0.07461 -0.0039 0.0020 0.9090 18.000 1.2452 0.08963 0.08521 -0.0085 0.0020 0.9109 18.500 1.2234 0.10135 0.09725 -0.0143 0.0020 0.9128 19.000 1.1968 0.11449 0.11071 -0.0214 0.0020 0.9145 19.500 1.1691 0.12831 0.12482 -0.0293 0.0020 0.9162 20.000 1.1412 0.14242 0.13920 -0.0378 0.0020 0.9183 20.500 1.1140 0.15658 0.15361 -0.0465 0.0020 0.9210 21.000 1.0903 0.17035 0.16761 -0.0553 0.0021 0.9240 21.500 1.0698 0.18383 0.18128 -0.0642 0.0021 0.9270 22.500 1.0354 0.20892 0.20670 -0.0799 0.0022 0.9361 23.000 1.0239 0.21997 0.21790 -0.0865 0.0022 0.9431 23.500 1.0153 0.23005 0.22809 -0.0923 0.0022 0.9539 24.000 1.0090 0.23902 0.23717 -0.0977 0.0023 1.0000