XFOIL Version 6.94 Calculated polar for: RAF 32 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6126 0.00836 0.00279 -0.1447 0.7299 0.5757 0.500 0.6609 0.00823 0.00291 -0.1431 0.7176 0.6568 1.000 0.7128 0.00817 0.00300 -0.1422 0.7063 0.7419 2.000 0.8453 0.00802 0.00321 -0.1469 0.6828 1.0000 2.500 0.8703 0.00820 0.00301 -0.1399 0.6181 1.0000 3.000 0.8902 0.00885 0.00325 -0.1323 0.5280 1.0000 3.500 0.8986 0.00998 0.00378 -0.1228 0.4208 1.0000 4.000 0.8843 0.01239 0.00512 -0.1100 0.2253 1.0000 4.500 0.8792 0.01492 0.00676 -0.0997 0.0520 1.0000 5.000 0.9085 0.01602 0.00770 -0.0954 0.0077 1.0000 5.500 0.9456 0.01677 0.00849 -0.0924 0.0078 1.0000 6.000 0.9822 0.01758 0.00935 -0.0894 0.0089 1.0000 6.500 1.0178 0.01848 0.01033 -0.0863 0.0103 1.0000 7.000 1.0485 0.01970 0.01167 -0.0826 0.0104 1.0000 7.500 1.0754 0.02121 0.01333 -0.0786 0.0102 1.0000 8.000 1.0987 0.02304 0.01531 -0.0743 0.0102 1.0000 8.500 1.1159 0.02539 0.01779 -0.0697 0.0099 1.0000 9.000 1.1281 0.02823 0.02073 -0.0650 0.0099 1.0000 9.500 1.1350 0.03168 0.02426 -0.0604 0.0096 1.0000 10.000 1.1448 0.03514 0.02779 -0.0563 0.0096 1.0000 10.500 1.1603 0.03883 0.03135 -0.0523 0.0090 1.0000 11.000 1.1788 0.04182 0.03463 -0.0497 0.0078 1.0000 13.000 1.2425 0.06103 0.05494 -0.0407 0.0014 1.0000 13.500 1.2327 0.06706 0.06134 -0.0389 0.0014 1.0000 14.000 1.2215 0.07417 0.06881 -0.0382 0.0013 1.0000 14.500 1.2060 0.08235 0.07736 -0.0386 0.0013 1.0000 15.000 1.1872 0.09174 0.08712 -0.0404 0.0013 1.0000 15.500 1.1655 0.10238 0.09810 -0.0436 0.0013 1.0000 16.000 1.1419 0.11421 0.11026 -0.0484 0.0013 1.0000 16.500 1.1173 0.12728 0.12366 -0.0549 0.0013 1.0000 17.000 1.0933 0.14135 0.13802 -0.0628 0.0013 1.0000 17.500 1.0697 0.15655 0.15348 -0.0720 0.0013 1.0000 18.000 1.0485 0.17261 0.16976 -0.0820 0.0014 1.0000 18.500 1.0312 0.18884 0.18616 -0.0917 0.0014 1.0000 19.000 1.0217 0.20340 0.20080 -0.0998 0.0015 1.0000