XFOIL Version 6.96 Calculated polar for: WB-135/35 13.5% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.6966 0.08469 0.08234 -0.0560 1.0000 0.0078 -14.750 -0.7114 0.07840 0.07598 -0.0595 1.0000 0.0079 -14.500 -0.7442 0.06973 0.06713 -0.0644 1.0000 0.0077 -14.250 -0.7267 0.06882 0.06632 -0.0653 1.0000 0.0081 -14.000 -0.7662 0.05999 0.05726 -0.0700 1.0000 0.0079 -13.750 -0.7828 0.05458 0.05174 -0.0730 1.0000 0.0078 -13.500 -0.7946 0.04988 0.04696 -0.0757 1.0000 0.0079 -13.250 -0.8064 0.04530 0.04229 -0.0782 1.0000 0.0079 -13.000 -0.8141 0.04128 0.03821 -0.0807 1.0000 0.0081 -12.750 -0.8326 0.03622 0.03301 -0.0834 1.0000 0.0080 -12.500 -0.8402 0.03269 0.02940 -0.0862 1.0000 0.0080 -12.250 -0.8579 0.03020 0.02678 -0.0848 0.9990 0.0081 -12.000 -0.8354 0.02803 0.02447 -0.0881 0.9944 0.0082 -11.750 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0.0151 1.0000 8.250 1.1414 0.01567 0.00897 -0.0552 0.0136 1.0000 8.500 1.1575 0.01611 0.00945 -0.0534 0.0132 1.0000 8.750 1.1728 0.01662 0.01000 -0.0515 0.0126 1.0000 9.000 1.1874 0.01718 0.01061 -0.0496 0.0121 1.0000 9.250 1.2012 0.01781 0.01128 -0.0477 0.0116 1.0000 9.500 1.2127 0.01861 0.01212 -0.0456 0.0109 1.0000 9.750 1.2217 0.01959 0.01318 -0.0432 0.0105 1.0000 10.000 1.2290 0.02072 0.01440 -0.0408 0.0101 1.0000 10.250 1.2448 0.02134 0.01505 -0.0396 0.0098 1.0000 10.500 1.2558 0.02230 0.01607 -0.0379 0.0096 1.0000 10.750 1.2665 0.02331 0.01713 -0.0363 0.0092 1.0000 11.000 1.2769 0.02438 0.01825 -0.0347 0.0089 1.0000 11.250 1.2837 0.02576 0.01971 -0.0330 0.0087 1.0000 11.500 1.2927 0.02702 0.02102 -0.0317 0.0085 1.0000 11.750 1.2979 0.02863 0.02268 -0.0302 0.0082 1.0000 12.000 1.3032 0.03028 0.02440 -0.0288 0.0080 1.0000 12.250 1.3031 0.03247 0.02668 -0.0274 0.0079 1.0000 12.500 1.2941 0.03554 0.02985 -0.0257 0.0076 1.0000 12.750 1.2958 0.03775 0.03213 -0.0247 0.0076 1.0000 13.000 1.2818 0.04153 0.03602 -0.0234 0.0075 1.0000 13.250 1.2962 0.04269 0.03724 -0.0231 0.0073 1.0000 13.500 1.2979 0.04512 0.03974 -0.0226 0.0072 1.0000 13.750 1.2937 0.04824 0.04295 -0.0220 0.0072 1.0000 14.000 1.3012 0.05025 0.04503 -0.0219 0.0069 1.0000 14.250 1.3037 0.05279 0.04764 -0.0218 0.0068 1.0000 14.500 1.2995 0.05615 0.05108 -0.0216 0.0067 1.0000 14.750 1.2993 0.05917 0.05418 -0.0217 0.0065 1.0000 15.000 1.2999 0.06217 0.05726 -0.0219 0.0064 1.0000 15.250 1.2971 0.06559 0.06076 -0.0221 0.0063 1.0000 15.500 1.2937 0.06920 0.06445 -0.0225 0.0062 1.0000 15.750 1.2927 0.07262 0.06794 -0.0231 0.0061 1.0000 16.000 1.2894 0.07632 0.07172 -0.0237 0.0060 1.0000 16.250 1.2858 0.08004 0.07551 -0.0242 0.0060 1.0000 16.500 1.2840 0.08375 0.07930 -0.0251 0.0059 1.0000 16.750 1.2812 0.08750 0.08312 -0.0259 0.0059 1.0000 17.000 1.2782 0.09145 0.08712 -0.0270 0.0057 1.0000 17.250 1.2750 0.09526 0.09101 -0.0278 0.0057 1.0000