XFOIL Version 6.94 Calculated polar for: WORTMANN FX 05-188 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 0.4552 0.01159 0.00622 -0.1093 0.6998 0.6905 0.500 0.5136 0.01171 0.00628 -0.1100 0.6927 0.6983 1.000 0.5718 0.01181 0.00633 -0.1109 0.6852 0.7054 1.500 0.6249 0.01180 0.00641 -0.1106 0.6777 0.7100 2.000 0.6824 0.01186 0.00648 -0.1111 0.6711 0.7152 2.500 0.7403 0.01202 0.00663 -0.1120 0.6645 0.7217 3.000 0.7951 0.01194 0.00664 -0.1123 0.6562 0.7270 3.500 0.8506 0.01190 0.00663 -0.1124 0.6485 0.7310 4.000 0.9029 0.01193 0.00676 -0.1120 0.6387 0.7354 4.500 0.9577 0.01184 0.00669 -0.1120 0.6276 0.7408 5.000 1.0094 0.01180 0.00670 -0.1116 0.6121 0.7457 5.500 1.0545 0.01170 0.00660 -0.1097 0.5896 0.7494 6.000 1.0971 0.01188 0.00679 -0.1074 0.5670 0.7530 6.500 1.1351 0.01222 0.00710 -0.1043 0.5414 0.7574 7.000 1.1646 0.01258 0.00747 -0.0997 0.5104 0.7622 7.500 1.1846 0.01325 0.00804 -0.0936 0.4739 0.7662 8.000 1.1851 0.01448 0.00911 -0.0846 0.4206 0.7702 8.500 1.1758 0.01653 0.01096 -0.0752 0.3673 0.7744 9.000 1.1592 0.01962 0.01373 -0.0665 0.2943 0.7787 9.500 1.1354 0.02379 0.01744 -0.0584 0.2106 0.7829 10.000 1.1231 0.02795 0.02119 -0.0527 0.1384 0.7861 10.500 1.1186 0.03193 0.02486 -0.0483 0.0858 0.7891 11.000 1.1256 0.03544 0.02828 -0.0454 0.0571 0.7917 11.500 1.1373 0.03887 0.03164 -0.0431 0.0408 0.7947 12.000 1.1525 0.04225 0.03507 -0.0414 0.0361 0.7982 12.500 1.1691 0.04576 0.03868 -0.0402 0.0337 0.8012 13.000 1.1785 0.05015 0.04315 -0.0391 0.0318 0.8040 13.500 1.1947 0.05413 0.04727 -0.0385 0.0304 0.8067 14.000 1.2077 0.05845 0.05173 -0.0381 0.0292 0.8100 14.500 1.2174 0.06334 0.05673 -0.0378 0.0283 0.8134 15.000 1.2277 0.06834 0.06184 -0.0378 0.0275 0.8170 15.500 1.2447 0.07277 0.06644 -0.0381 0.0268 0.8216 16.500 1.2796 0.08169 0.07564 -0.0393 0.0253 0.8304 17.000 1.2983 0.08596 0.08003 -0.0400 0.0246 0.8356 17.500 1.3291 0.08857 0.08264 -0.0399 0.0238 0.8412 18.000 1.3440 0.09364 0.08797 -0.0412 0.0235 0.8475 18.500 1.3536 0.09941 0.09404 -0.0428 0.0230 0.8549 19.000 1.3635 0.10532 0.10020 -0.0448 0.0223 0.8632 19.500 1.3719 0.11119 0.10633 -0.0468 0.0218 0.8734 20.000 1.3771 0.11758 0.11295 -0.0493 0.0213 0.8863 20.500 1.3797 0.12363 0.11926 -0.0513 0.0209 0.9101 21.500 1.3801 0.13634 0.13240 -0.0565 0.0202 1.0000 22.000 1.3613 0.14735 0.14376 -0.0633 0.0201 1.0000 22.500 1.3367 0.15972 0.15648 -0.0715 0.0200 1.0000 23.000 1.3057 0.17380 0.17091 -0.0814 0.0200 1.0000 23.500 1.2638 0.19093 0.18841 -0.0938 0.0201 1.0000 24.500 0.8577 0.31840 0.31693 -0.1563 0.0183 0.8201 25.000 0.8716 0.32397 0.32254 -0.1592 0.0170 0.8237 25.500 0.8716 0.34012 0.33871 -0.1648 0.0155 0.8252 26.000 0.8793 0.34915 0.34778 -0.1684 0.0143 0.8285 26.500 0.8896 0.35529 0.35397 -0.1709 0.0137 0.8326 27.000 0.8901 0.37100 0.36970 -0.1758 0.0131 0.8352 27.500 0.8962 0.38175 0.38048 -0.1797 0.0120 0.8391 28.000 0.9032 0.39175 0.39050 -0.1835 0.0114 0.8434 28.500 0.9096 0.40013 0.39893 -0.1866 0.0110 0.8482 29.000 0.9163 0.40773 0.40657 -0.1891 0.0108 0.8540 29.500 0.9189 0.42050 0.41936 -0.1931 0.0107 0.8590 30.500 0.9252 0.44318 0.44211 -0.2000 0.0096 0.8700 31.000 0.9286 0.45225 0.45122 -0.2029 0.0089 0.8772 31.500 0.9321 0.46093 0.45993 -0.2058 0.0085 0.8846 32.000 0.9334 0.46656 0.46561 -0.2073 0.0083 0.8941 33.000 0.9324 0.48753 0.48662 -0.2120 0.0073 0.9117 33.500 0.9304 0.49322 0.49233 -0.2131 0.0066 0.9241 34.000 0.9171 0.48913 0.48823 -0.2097 0.0064 0.9536