XFOIL Version 6.96 Calculated polar for: RAF 38 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -16.500 -0.7122 0.12374 0.12094 -0.0233 1.0000 0.0109 -16.250 -0.7546 0.11079 0.10787 -0.0299 1.0000 0.0109 -16.000 -0.7926 0.09959 0.09659 -0.0358 1.0000 0.0108 -15.750 -0.8395 0.08744 0.08432 -0.0425 1.0000 0.0106 -15.500 -0.8913 0.07460 0.07132 -0.0499 1.0000 0.0105 -15.250 -0.9410 0.06181 0.05834 -0.0580 1.0000 0.0102 -15.000 -0.9754 0.05143 0.04774 -0.0657 1.0000 0.0101 -14.750 -0.9958 0.04421 0.04032 -0.0713 1.0000 0.0100 -14.500 -1.0088 0.03928 0.03521 -0.0746 1.0000 0.0102 -14.250 -1.0191 0.03566 0.03143 -0.0759 1.0000 0.0102 -14.000 -1.0227 0.03329 0.02893 -0.0756 1.0000 0.0104 -13.750 -1.0266 0.03129 0.02680 -0.0743 1.0000 0.0105 -13.500 -1.0273 0.02979 0.02518 -0.0722 1.0000 0.0107 -13.250 -1.0284 0.02849 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0.4680 0.00732 0.00210 -0.0445 0.5359 0.9374 2.250 0.5044 0.00746 0.00219 -0.0463 0.5189 0.9510 2.500 0.5410 0.00763 0.00228 -0.0482 0.4995 0.9598 2.750 0.5737 0.00781 0.00238 -0.0493 0.4821 0.9671 3.000 0.6039 0.00799 0.00249 -0.0498 0.4667 0.9742 3.250 0.6381 0.00815 0.00260 -0.0513 0.4541 0.9780 3.500 0.6698 0.00833 0.00273 -0.0522 0.4414 0.9831 3.750 0.7027 0.00853 0.00286 -0.0534 0.4256 0.9870 4.000 0.7365 0.00873 0.00301 -0.0549 0.4099 0.9910 4.250 0.7720 0.00890 0.00315 -0.0567 0.3984 0.9952 4.500 0.8109 0.00908 0.00330 -0.0593 0.3834 0.9992 4.750 0.8361 0.00928 0.00345 -0.0589 0.3676 1.0000 5.000 0.8569 0.00947 0.00361 -0.0576 0.3527 1.0000 5.250 0.8773 0.00969 0.00378 -0.0562 0.3360 1.0000 5.500 0.8960 0.01000 0.00399 -0.0545 0.3099 1.0000 5.750 0.9130 0.01042 0.00426 -0.0526 0.2772 1.0000 6.000 0.9295 0.01087 0.00457 -0.0506 0.2485 1.0000 6.250 0.9467 0.01129 0.00488 -0.0487 0.2264 1.0000 6.500 0.9641 0.01169 0.00521 -0.0468 0.2069 1.0000 6.750 0.9811 0.01211 0.00554 -0.0449 0.1857 1.0000 7.000 0.9965 0.01262 0.00593 -0.0428 0.1599 1.0000 7.250 1.0074 0.01336 0.00644 -0.0399 0.1183 1.0000 7.500 1.0176 0.01412 0.00701 -0.0370 0.0876 1.0000 7.750 1.0323 0.01463 0.00745 -0.0348 0.0767 1.0000 8.000 1.0490 0.01501 0.00785 -0.0329 0.0717 1.0000 8.250 1.0640 0.01546 0.00828 -0.0308 0.0671 1.0000 8.500 1.0802 0.01583 0.00868 -0.0288 0.0637 1.0000 8.750 1.0941 0.01623 0.00911 -0.0264 0.0608 1.0000 9.000 1.1055 0.01668 0.00957 -0.0237 0.0577 1.0000 9.250 1.1174 0.01713 0.01005 -0.0211 0.0549 1.0000 9.500 1.1319 0.01753 0.01049 -0.0190 0.0523 1.0000 9.750 1.1450 0.01802 0.01101 -0.0168 0.0489 1.0000 10.000 1.1567 0.01862 0.01161 -0.0146 0.0447 1.0000 10.250 1.1708 0.01915 0.01220 -0.0128 0.0418 1.0000 10.500 1.1825 0.01983 0.01287 -0.0109 0.0364 1.0000 10.750 1.1936 0.02060 0.01364 -0.0090 0.0319 1.0000 11.000 1.2032 0.02150 0.01453 -0.0071 0.0278 1.0000 11.250 1.2133 0.02243 0.01549 -0.0054 0.0250 1.0000 11.500 1.2220 0.02352 0.01660 -0.0038 0.0227 1.0000 11.750 1.2313 0.02462 0.01777 -0.0023 0.0209 1.0000 12.000 1.2399 0.02584 0.01903 -0.0009 0.0193 1.0000 12.250 1.2473 0.02720 0.02043 0.0003 0.0181 1.0000 12.500 1.2554 0.02856 0.02186 0.0015 0.0171 1.0000 12.750 1.2636 0.02996 0.02333 0.0025 0.0163 1.0000 13.000 1.2707 0.03149 0.02493 0.0034 0.0155 1.0000 13.250 1.2764 0.03319 0.02668 0.0042 0.0149 1.0000 13.500 1.2803 0.03510 0.02864 0.0050 0.0142 1.0000 13.750 1.2864 0.03687 0.03050 0.0057 0.0137 1.0000 14.000 1.2908 0.03882 0.03255 0.0063 0.0133 1.0000 14.250 1.2947 0.04087 0.03468 0.0067 0.0127 1.0000 14.500 1.2965 0.04319 0.03708 0.0071 0.0123 1.0000 14.750 1.2985 0.04554 0.03950 0.0074 0.0120 1.0000 15.000 1.2979 0.04824 0.04228 0.0075 0.0116 1.0000 15.250 1.2976 0.05103 0.04515 0.0075 0.0113 1.0000 15.500 1.2988 0.05371 0.04793 0.0073 0.0111 1.0000 15.750 1.2982 0.05666 0.05098 0.0071 0.0107 1.0000 16.000 1.2975 0.05972 0.05414 0.0067 0.0104 1.0000 16.250 1.2950 0.06310 0.05762 0.0061 0.0103 1.0000 16.500 1.2932 0.06645 0.06106 0.0054 0.0100 1.0000 16.750 1.2880 0.07033 0.06504 0.0044 0.0099 1.0000 17.000 1.2853 0.07397 0.06877 0.0035 0.0096 1.0000 17.250 1.2789 0.07820 0.07310 0.0023 0.0095 1.0000 17.500 1.2711 0.08269 0.07769 0.0009 0.0093 1.0000 17.750 1.2621 0.08747 0.08256 -0.0007 0.0092 1.0000 18.000 1.2548 0.09206 0.08726 -0.0023 0.0091 1.0000 18.250 1.2482 0.09659 0.09190 -0.0039 0.0090 1.0000 18.500 1.2404 0.10138 0.09681 -0.0058 0.0089 1.0000 18.750 1.2328 0.10627 0.10181 -0.0077 0.0087 1.0000 19.000 1.2238 0.11147 0.10712 -0.0099 0.0086 1.0000 19.250 1.2145 0.11675 0.11251 -0.0122 0.0085 1.0000