XFOIL Version 6.96 Calculated polar for: Falcon 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.8867 0.11589 0.11301 -0.0108 1.0000 0.0122 -16.500 -0.9969 0.08893 0.08565 -0.0256 1.0000 0.0118 -16.250 -1.0444 0.07557 0.07204 -0.0337 1.0000 0.0117 -16.000 -1.0739 0.06644 0.06271 -0.0393 1.0000 0.0117 -15.750 -1.0935 0.05953 0.05562 -0.0434 1.0000 0.0117 -15.500 -1.1074 0.05400 0.04992 -0.0463 1.0000 0.0118 -15.250 -1.1173 0.04945 0.04522 -0.0484 1.0000 0.0119 -15.000 -1.1235 0.04575 0.04138 -0.0495 1.0000 0.0120 -14.750 -1.1285 0.04250 0.03800 -0.0500 1.0000 0.0121 -14.500 -1.1311 0.03978 0.03513 -0.0499 1.0000 0.0122 -14.250 -1.1314 0.03748 0.03271 -0.0492 1.0000 0.0124 -14.000 -1.1312 0.03541 0.03050 -0.0481 1.0000 0.0126 -13.750 -1.1290 0.03364 0.02861 -0.0467 1.0000 0.0128 -13.500 -1.1256 0.03208 0.02693 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0.2328 0.00801 0.00206 0.0001 0.4329 0.8620 1.750 0.2611 0.00809 0.00211 0.0001 0.4205 0.8738 2.000 0.2897 0.00818 0.00217 0.0000 0.4081 0.8854 2.250 0.3188 0.00827 0.00223 -0.0003 0.3958 0.8972 2.500 0.3502 0.00837 0.00230 -0.0010 0.3840 0.9084 2.750 0.3834 0.00849 0.00239 -0.0023 0.3719 0.9187 3.000 0.4174 0.00863 0.00248 -0.0037 0.3600 0.9295 3.250 0.4569 0.00877 0.00259 -0.0064 0.3482 0.9387 3.500 0.4974 0.00894 0.00273 -0.0093 0.3365 0.9458 3.750 0.5385 0.00913 0.00286 -0.0124 0.3246 0.9507 4.000 0.5752 0.00931 0.00301 -0.0145 0.3141 0.9561 4.250 0.6136 0.00950 0.00317 -0.0170 0.3025 0.9590 4.500 0.6500 0.00971 0.00334 -0.0190 0.2915 0.9623 4.750 0.6844 0.00993 0.00352 -0.0205 0.2814 0.9665 5.000 0.7192 0.01013 0.00371 -0.0222 0.2714 0.9702 5.250 0.7535 0.01036 0.00391 -0.0237 0.2611 0.9742 5.500 0.7856 0.01062 0.00413 -0.0248 0.2498 0.9794 5.750 0.8157 0.01087 0.00435 -0.0255 0.2391 0.9869 6.000 0.8443 0.01114 0.00461 -0.0259 0.2301 0.9952 6.250 0.8769 0.01140 0.00483 -0.0272 0.2201 0.9979 6.500 0.9101 0.01165 0.00507 -0.0286 0.2105 0.9997 6.750 0.9335 0.01188 0.00528 -0.0279 0.2024 1.0000 7.000 0.9541 0.01214 0.00551 -0.0266 0.1928 1.0000 7.250 0.9749 0.01243 0.00576 -0.0254 0.1813 1.0000 7.500 0.9957 0.01275 0.00603 -0.0242 0.1698 1.0000 7.750 1.0165 0.01308 0.00632 -0.0230 0.1599 1.0000 8.000 1.0375 0.01342 0.00663 -0.0219 0.1506 1.0000 8.250 1.0590 0.01373 0.00694 -0.0208 0.1433 1.0000 8.500 1.0801 0.01408 0.00728 -0.0197 0.1363 1.0000 8.750 1.1014 0.01442 0.00761 -0.0186 0.1293 1.0000 9.000 1.1214 0.01485 0.00801 -0.0174 0.1199 1.0000 9.250 1.1416 0.01526 0.00840 -0.0162 0.1103 1.0000 9.500 1.1612 0.01571 0.00883 -0.0149 0.1002 1.0000 9.750 1.1783 0.01633 0.00936 -0.0133 0.0848 1.0000 10.000 1.1875 0.01746 0.01026 -0.0106 0.0511 1.0000 10.250 1.1925 0.01882 0.01146 -0.0073 0.0261 1.0000 10.500 1.2058 0.01957 0.01222 -0.0051 0.0214 1.0000 10.750 1.2200 0.02024 0.01292 -0.0031 0.0191 1.0000 11.000 1.2326 0.02095 0.01367 -0.0009 0.0174 1.0000 11.250 1.2408 0.02166 0.01444 0.0021 0.0162 1.0000 11.500 1.2498 0.02233 0.01518 0.0049 0.0154 1.0000 11.750 1.2582 0.02311 0.01602 0.0076 0.0146 1.0000 12.000 1.2653 0.02405 0.01701 0.0101 0.0138 1.0000 12.250 1.2711 0.02516 0.01820 0.0124 0.0133 1.0000 12.500 1.2773 0.02637 0.01948 0.0144 0.0129 1.0000 12.750 1.2841 0.02762 0.02082 0.0161 0.0125 1.0000 13.000 1.2899 0.02906 0.02235 0.0175 0.0122 1.0000 13.250 1.2944 0.03072 0.02411 0.0187 0.0118 1.0000 13.500 1.2979 0.03262 0.02610 0.0196 0.0116 1.0000 13.750 1.3004 0.03476 0.02834 0.0202 0.0113 1.0000 14.000 1.3011 0.03726 0.03093 0.0204 0.0110 1.0000 14.250 1.2999 0.04012 0.03390 0.0203 0.0109 1.0000 14.500 1.2970 0.04334 0.03723 0.0199 0.0107 1.0000 14.750 1.2912 0.04706 0.04105 0.0191 0.0105 1.0000 15.000 1.2829 0.05121 0.04532 0.0181 0.0104 1.0000 15.250 1.2714 0.05591 0.05014 0.0167 0.0102 1.0000 15.500 1.2609 0.06053 0.05489 0.0154 0.0102 1.0000 15.750 1.2498 0.06536 0.05984 0.0138 0.0101 1.0000 16.000 1.2387 0.07029 0.06490 0.0122 0.0100 1.0000 16.250 1.2269 0.07545 0.07017 0.0104 0.0099 1.0000 16.500 1.2135 0.08097 0.07581 0.0084 0.0099 1.0000 16.750 1.2006 0.08649 0.08145 0.0063 0.0098 1.0000