XFOIL Version 6.96 Calculated polar for: FX 84-W-097 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.4962 0.10654 0.10426 -0.0110 1.0000 0.0085 -10.750 -0.4979 0.10150 0.09923 -0.0134 1.0000 0.0086 -9.750 -0.7241 0.03120 0.02800 -0.0570 0.9513 0.0083 -9.500 -0.7160 0.02760 0.02388 -0.0565 0.9276 0.0085 -9.250 -0.7057 0.02473 0.02058 -0.0555 0.9106 0.0087 -9.000 -0.6884 0.02322 0.01883 -0.0546 0.8975 0.0090 -8.500 -0.6456 0.02137 0.01665 -0.0535 0.8756 0.0096 -8.250 -0.6232 0.02042 0.01551 -0.0530 0.8662 0.0099 -7.750 -0.5777 0.01815 0.01276 -0.0520 0.8481 0.0107 -7.500 -0.5539 0.01716 0.01153 -0.0516 0.8401 0.0111 -7.250 -0.5293 0.01630 0.01046 -0.0512 0.8318 0.0115 -7.000 -0.5041 0.01560 0.00958 -0.0509 0.8242 0.0118 -6.750 -0.4795 0.01466 0.00851 -0.0505 0.8164 0.0125 -6.500 -0.4535 0.01414 0.00789 -0.0503 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1.0000 13.250 1.3197 0.04004 0.03445 -0.0157 0.0066 1.0000 13.500 1.3226 0.04236 0.03687 -0.0154 0.0065 1.0000 13.750 1.3242 0.04490 0.03951 -0.0152 0.0063 1.0000 14.000 1.3240 0.04772 0.04245 -0.0152 0.0062 1.0000 14.250 1.3212 0.05096 0.04580 -0.0154 0.0061 1.0000 14.500 1.3157 0.05463 0.04960 -0.0157 0.0060 1.0000 14.750 1.3104 0.05844 0.05354 -0.0163 0.0059 1.0000 15.000 1.3103 0.06175 0.05700 -0.0171 0.0059 1.0000 15.250 1.3069 0.06564 0.06104 -0.0182 0.0058 1.0000 15.500 1.3023 0.06989 0.06544 -0.0196 0.0057 1.0000 15.750 1.2969 0.07439 0.07010 -0.0212 0.0056 1.0000 16.000 1.2907 0.07920 0.07507 -0.0231 0.0056 1.0000 16.250 1.2819 0.08464 0.08067 -0.0254 0.0055 1.0000 16.500 1.2732 0.09026 0.08645 -0.0281 0.0055 1.0000 16.750 1.2624 0.09648 0.09283 -0.0311 0.0054 1.0000 17.000 1.2506 0.10312 0.09964 -0.0345 0.0054 1.0000 17.250 1.2373 0.11034 0.10703 -0.0385 0.0053 1.0000 17.500 1.2236 0.11779 0.11463 -0.0426 0.0053 1.0000 17.750 1.2086 0.12592 0.12292 -0.0473 0.0053 1.0000 18.000 1.1918 0.13471 0.13187 -0.0525 0.0053 1.0000 18.250 1.1738 0.14420 0.14153 -0.0582 0.0053 1.0000 18.500 1.1542 0.15451 0.15198 -0.0645 0.0054 1.0000 18.750 1.1280 0.16733 0.16497 -0.0724 0.0054 1.0000