XFOIL Version 6.94 Calculated polar for: SPICA 11.73% 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 0.4720 0.01091 0.00327 -0.0831 0.5965 0.0452 0.500 0.5248 0.01068 0.00301 -0.0822 0.5856 0.0544 1.000 0.5625 0.00886 0.00287 -0.0791 0.5741 0.6337 1.500 0.6977 0.00832 0.00297 -0.0956 0.5601 1.0000 2.000 0.7451 0.00848 0.00299 -0.0937 0.5486 1.0000 2.500 0.7930 0.00861 0.00308 -0.0920 0.5368 1.0000 3.000 0.8409 0.00880 0.00319 -0.0902 0.5247 1.0000 3.500 0.8884 0.00900 0.00330 -0.0884 0.5109 1.0000 4.000 0.9363 0.00917 0.00346 -0.0867 0.4960 1.0000 4.500 0.9835 0.00939 0.00364 -0.0849 0.4791 1.0000 5.000 1.0302 0.00966 0.00387 -0.0831 0.4612 1.0000 5.500 1.0753 0.01000 0.00414 -0.0810 0.4405 1.0000 6.000 1.1201 0.01038 0.00450 -0.0789 0.4184 1.0000 6.500 1.1635 0.01084 0.00491 -0.0766 0.3937 1.0000 7.000 1.2043 0.01143 0.00542 -0.0739 0.3675 1.0000 7.500 1.2450 0.01203 0.00598 -0.0713 0.3414 1.0000 8.500 1.3167 0.01357 0.00739 -0.0646 0.2899 1.0000 9.000 1.3455 0.01447 0.00822 -0.0601 0.2662 1.0000 9.500 1.3709 0.01538 0.00911 -0.0551 0.2475 1.0000 10.000 1.3970 0.01636 0.01011 -0.0505 0.2306 1.0000 10.500 1.4223 0.01747 0.01126 -0.0462 0.2147 1.0000 11.000 1.4440 0.01886 0.01266 -0.0419 0.1967 1.0000 11.500 1.4645 0.02049 0.01433 -0.0381 0.1769 1.0000 12.000 1.4776 0.02281 0.01661 -0.0342 0.1509 1.0000 12.500 1.4789 0.02634 0.02002 -0.0303 0.1183 1.0000 13.000 1.4592 0.03212 0.02554 -0.0265 0.0709 1.0000 13.500 1.4295 0.03953 0.03274 -0.0238 0.0339 1.0000 14.000 1.4142 0.04615 0.03942 -0.0225 0.0249 1.0000 14.500 1.4079 0.05223 0.04570 -0.0219 0.0221 1.0000 15.000 1.3973 0.05919 0.05284 -0.0219 0.0204 1.0000 15.500 1.3772 0.06774 0.06160 -0.0228 0.0190 1.0000 16.000 1.3672 0.07545 0.06954 -0.0240 0.0181 1.0000 16.500 1.3523 0.08412 0.07843 -0.0258 0.0175 1.0000 17.000 1.3351 0.09353 0.08805 -0.0282 0.0169 1.0000 17.500 1.3182 0.10313 0.09783 -0.0311 0.0163 1.0000 18.000 1.3000 0.11323 0.10811 -0.0346 0.0158 1.0000 18.500 1.2856 0.12264 0.11764 -0.0379 0.0152 1.0000 19.000 1.2813 0.13046 0.12560 -0.0408 0.0148 1.0000 19.500 1.2813 0.13775 0.13306 -0.0438 0.0144 1.0000 20.000 1.2826 0.14487 0.14033 -0.0471 0.0138 1.0000 20.500 1.2849 0.15171 0.14731 -0.0503 0.0133 1.0000 21.000 1.2864 0.15881 0.15453 -0.0540 0.0126 1.0000 21.500 1.2911 0.16510 0.16092 -0.0574 0.0123 1.0000 22.000 1.2989 0.17023 0.16614 -0.0599 0.0118 1.0000 22.500 1.2999 0.17684 0.17296 -0.0634 0.0115 1.0000 23.000 1.2915 0.18670 0.18307 -0.0699 0.0114 1.0000 23.500 1.2779 0.19808 0.19472 -0.0775 0.0113 1.0000 24.000 1.2612 0.21050 0.20741 -0.0859 0.0113 1.0000 24.500 1.2373 0.22562 0.22281 -0.0960 0.0114 1.0000 25.000 1.1999 0.24657 0.24405 -0.1092 0.0116 1.0000 25.500 0.8631 0.30732 0.30559 -0.1302 0.0168 1.0000 26.000 0.8709 0.31440 0.31270 -0.1333 0.0156 1.0000 26.500 0.8820 0.31993 0.31826 -0.1353 0.0151 1.0000 27.000 0.8789 0.33566 0.33399 -0.1409 0.0139 1.0000 27.500 0.8844 0.34428 0.34264 -0.1443 0.0126 1.0000 28.000 0.8909 0.35161 0.35001 -0.1473 0.0119 1.0000 28.500 0.8987 0.35938 0.35780 -0.1497 0.0115 1.0000 29.000 0.8981 0.37313 0.37156 -0.1545 0.0110 1.0000 29.500 0.9022 0.38312 0.38158 -0.1579 0.0097 1.0000 30.000 0.9064 0.39196 0.39045 -0.1611 0.0094 1.0000 30.500 0.9107 0.40006 0.39858 -0.1642 0.0089 1.0000 31.000 0.9173 0.40677 0.40533 -0.1664 0.0086 1.0000 31.500 0.9184 0.41812 0.41670 -0.1701 0.0086 1.0000 32.000 0.9194 0.43102 0.42962 -0.1740 0.0079 1.0000 32.500 0.9221 0.44067 0.43930 -0.1772 0.0072 1.0000 33.000 0.9245 0.44970 0.44835 -0.1803 0.0068 1.0000 33.500 0.9266 0.45788 0.45657 -0.1833 0.0065 1.0000 34.000 0.9290 0.46540 0.46413 -0.1860 0.0063 1.0000 34.500 0.9302 0.47581 0.47456 -0.1890 0.0062 1.0000