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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.5292 0.11752 0.11503 -0.0400 1.0000 0.0064 -14.750 -0.6222 0.09371 0.09082 -0.0516 1.0000 0.0058 -14.500 -0.6397 0.08666 0.08367 -0.0552 1.0000 0.0058 -14.250 -0.6501 0.08115 0.07811 -0.0581 1.0000 0.0060 -14.000 -0.6650 0.07512 0.07199 -0.0613 1.0000 0.0060 -13.750 -0.6787 0.06970 0.06650 -0.0642 1.0000 0.0060 -13.500 -0.6978 0.06374 0.06043 -0.0672 1.0000 0.0060 -13.250 -0.7098 0.05895 0.05557 -0.0697 1.0000 0.0060 -13.000 -0.7312 0.05320 0.04968 -0.0724 1.0000 0.0059 -12.750 -0.7431 0.04879 0.04520 -0.0745 1.0000 0.0059 -12.500 -0.7528 0.04473 0.04110 -0.0765 1.0000 0.0061 -12.250 -0.7722 0.03993 0.03617 -0.0784 1.0000 0.0060 -12.000 -0.7756 0.03587 0.03202 -0.0823 0.9988 0.0061 -11.500 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1.0000 8.750 1.1315 0.01961 0.01195 -0.0466 0.0114 1.0000 9.000 1.1451 0.02030 0.01270 -0.0448 0.0104 1.0000 9.250 1.1578 0.02109 0.01355 -0.0430 0.0099 1.0000 9.500 1.1673 0.02211 0.01465 -0.0409 0.0092 1.0000 9.750 1.1796 0.02298 0.01558 -0.0393 0.0088 1.0000 10.000 1.1915 0.02390 0.01657 -0.0377 0.0085 1.0000 10.250 1.2036 0.02483 0.01755 -0.0363 0.0079 1.0000 10.500 1.2137 0.02594 0.01875 -0.0348 0.0076 1.0000 10.750 1.2228 0.02716 0.02004 -0.0333 0.0074 1.0000 11.000 1.2318 0.02843 0.02136 -0.0319 0.0070 1.0000 11.250 1.2374 0.03003 0.02303 -0.0304 0.0067 1.0000 11.500 1.2407 0.03186 0.02495 -0.0290 0.0066 1.0000 11.750 1.2424 0.03392 0.02709 -0.0276 0.0064 1.0000 12.000 1.2482 0.03567 0.02894 -0.0266 0.0061 1.0000 12.250 1.2504 0.03781 0.03118 -0.0256 0.0061 1.0000 12.500 1.2527 0.04002 0.03348 -0.0247 0.0060 1.0000 12.750 1.2546 0.04232 0.03587 -0.0240 0.0057 1.0000 13.000 1.2529 0.04507 0.03874 -0.0233 0.0057 1.0000 13.250 1.2512 0.04794 0.04170 -0.0228 0.0056 1.0000 13.500 1.2509 0.05073 0.04459 -0.0225 0.0054 1.0000 13.750 1.2490 0.05380 0.04775 -0.0224 0.0054 1.0000 14.000 1.2479 0.05689 0.05092 -0.0224 0.0052 1.0000 14.250 1.2494 0.05972 0.05384 -0.0225 0.0050 1.0000 14.500 1.2450 0.06337 0.05758 -0.0228 0.0049 1.0000 14.750 1.2398 0.06723 0.06154 -0.0233 0.0049 1.0000 15.000 1.2396 0.07057 0.06494 -0.0239 0.0047 1.0000 15.250 1.2356 0.07447 0.06893 -0.0247 0.0047 1.0000 15.500 1.2264 0.07912 0.07367 -0.0256 0.0046 1.0000 15.750 1.2208 0.08337 0.07801 -0.0265 0.0046 1.0000 16.000 1.2123 0.08801 0.08273 -0.0276 0.0045 1.0000