XFOIL Version 6.96 Calculated polar for: GOE 599 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.9655 0.08113 0.07891 -0.0290 1.0000 0.0036 -14.750 -1.0193 0.06641 0.06403 -0.0376 1.0000 0.0034 -14.500 -1.0704 0.05076 0.04812 -0.0497 1.0000 0.0034 -14.250 -1.0908 0.04243 0.03957 -0.0573 1.0000 0.0034 -14.000 -1.1027 0.03723 0.03418 -0.0613 1.0000 0.0034 -13.750 -1.1093 0.03408 0.03087 -0.0621 1.0000 0.0034 -13.500 -1.1148 0.03187 0.02851 -0.0605 1.0000 0.0034 -13.250 -1.1147 0.03026 0.02677 -0.0583 1.0000 0.0035 -13.000 -1.1123 0.02848 0.02484 -0.0563 1.0000 0.0035 -12.750 -1.1102 0.02668 0.02286 -0.0538 1.0000 0.0036 -12.500 -1.1028 0.02530 0.02135 -0.0516 1.0000 0.0037 -12.250 -1.0921 0.02419 0.02013 -0.0496 1.0000 0.0038 -12.000 -1.0798 0.02320 0.01904 -0.0477 1.0000 0.0039 -11.750 -1.0661 0.02230 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0.00235 -0.0480 0.0521 0.9064 3.000 0.5195 0.00874 0.00250 -0.0478 0.0509 0.9722 3.250 0.5549 0.00889 0.00265 -0.0496 0.0494 0.9904 3.500 0.5884 0.00907 0.00282 -0.0510 0.0476 0.9986 3.750 0.6155 0.00925 0.00298 -0.0509 0.0459 1.0000 4.000 0.6412 0.00944 0.00317 -0.0505 0.0445 1.0000 4.250 0.6670 0.00965 0.00339 -0.0502 0.0431 1.0000 4.500 0.6925 0.00991 0.00366 -0.0498 0.0417 1.0000 4.750 0.7181 0.01017 0.00395 -0.0494 0.0409 1.0000 5.000 0.7444 0.01034 0.00413 -0.0492 0.0406 1.0000 5.250 0.7709 0.01048 0.00428 -0.0490 0.0398 1.0000 5.500 0.7974 0.01063 0.00443 -0.0488 0.0385 1.0000 5.750 0.8237 0.01081 0.00461 -0.0487 0.0369 1.0000 6.000 0.8498 0.01101 0.00480 -0.0484 0.0353 1.0000 6.250 0.8756 0.01124 0.00503 -0.0482 0.0335 1.0000 6.500 0.9012 0.01149 0.00528 -0.0479 0.0317 1.0000 6.750 0.9274 0.01167 0.00548 -0.0477 0.0299 1.0000 7.000 0.9531 0.01189 0.00566 -0.0474 0.0253 1.0000 7.250 0.9775 0.01225 0.00594 -0.0470 0.0169 1.0000 7.500 1.0012 0.01269 0.00635 -0.0464 0.0123 1.0000 7.750 1.0252 0.01308 0.00678 -0.0458 0.0106 1.0000 8.000 1.0485 0.01355 0.00727 -0.0451 0.0090 1.0000 8.250 1.0720 0.01398 0.00773 -0.0445 0.0081 1.0000 8.500 1.0956 0.01438 0.00818 -0.0439 0.0076 1.0000 8.750 1.1187 0.01483 0.00867 -0.0432 0.0070 1.0000 9.000 1.1412 0.01533 0.00920 -0.0425 0.0065 1.0000 9.250 1.1628 0.01591 0.00983 -0.0416 0.0060 1.0000 9.500 1.1842 0.01649 0.01049 -0.0406 0.0056 1.0000 9.750 1.2062 0.01699 0.01104 -0.0398 0.0054 1.0000 10.000 1.2276 0.01752 0.01162 -0.0390 0.0051 1.0000 10.250 1.2485 0.01808 0.01224 -0.0380 0.0048 1.0000 10.500 1.2688 0.01868 0.01289 -0.0370 0.0046 1.0000 10.750 1.2883 0.01933 0.01360 -0.0359 0.0044 1.0000 11.000 1.3067 0.02005 0.01439 -0.0346 0.0041 1.0000 11.250 1.3234 0.02091 0.01533 -0.0331 0.0039 1.0000 11.500 1.3389 0.02183 0.01635 -0.0314 0.0038 1.0000 11.750 1.3553 0.02257 0.01718 -0.0299 0.0037 1.0000 12.000 1.3691 0.02335 0.01806 -0.0279 0.0036 1.0000 12.250 1.3810 0.02421 0.01901 -0.0257 0.0035 1.0000 12.500 1.3921 0.02513 0.02002 -0.0235 0.0034 1.0000 12.750 1.4022 0.02612 0.02112 -0.0212 0.0034 1.0000 13.000 1.4114 0.02721 0.02231 -0.0190 0.0033 1.0000 13.250 1.4194 0.02840 0.02360 -0.0169 0.0032 1.0000 13.500 1.4266 0.02967 0.02499 -0.0148 0.0031 1.0000 13.750 1.4328 0.03107 0.02651 -0.0128 0.0031 1.0000 14.000 1.4377 0.03262 0.02817 -0.0109 0.0030 1.0000 14.250 1.4414 0.03434 0.03001 -0.0093 0.0029 1.0000 14.500 1.4436 0.03628 0.03206 -0.0078 0.0029 1.0000 14.750 1.4448 0.03844 0.03435 -0.0066 0.0028 1.0000 15.000 1.4440 0.04090 0.03693 -0.0056 0.0028 1.0000 15.250 1.4411 0.04372 0.03988 -0.0050 0.0028 1.0000 15.500 1.4366 0.04689 0.04318 -0.0048 0.0027 1.0000 15.750 1.4298 0.05054 0.04697 -0.0050 0.0027 1.0000 16.000 1.4203 0.05480 0.05138 -0.0058 0.0027 1.0000 16.250 1.4079 0.05973 0.05646 -0.0073 0.0027 1.0000 16.500 1.3930 0.06547 0.06234 -0.0096 0.0026 1.0000 16.750 1.3729 0.07252 0.06957 -0.0130 0.0026 1.0000 17.000 1.3487 0.08082 0.07804 -0.0173 0.0026 1.0000 17.250 1.3178 0.09094 0.08835 -0.0229 0.0027 1.0000 17.500 1.2740 0.10409 0.10172 -0.0300 0.0027 1.0000 17.750 1.1736 0.13130 0.12929 -0.0441 0.0029 1.0000