XFOIL Version 6.96 Calculated polar for: GOE 600 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -1.0598 0.09369 0.09089 -0.0215 1.0000 0.0055 -17.000 -1.1221 0.07867 0.07566 -0.0297 1.0000 0.0054 -16.750 -1.1667 0.06717 0.06397 -0.0363 1.0000 0.0053 -16.500 -1.1959 0.05852 0.05513 -0.0416 1.0000 0.0053 -16.250 -1.2159 0.05161 0.04807 -0.0460 1.0000 0.0053 -16.000 -1.2279 0.04616 0.04247 -0.0494 1.0000 0.0053 -15.750 -1.2353 0.04156 0.03773 -0.0523 1.0000 0.0054 -15.500 -1.2383 0.03780 0.03384 -0.0545 1.0000 0.0054 -15.250 -1.2379 0.03475 0.03066 -0.0560 1.0000 0.0055 -15.000 -1.2358 0.03222 0.02802 -0.0567 1.0000 0.0055 -14.750 -1.2318 0.03020 0.02589 -0.0568 1.0000 0.0056 -14.500 -1.2308 0.02821 0.02379 -0.0560 1.0000 0.0057 -14.250 -1.2283 0.02662 0.02209 -0.0544 1.0000 0.0058 -14.000 -1.2232 0.02539 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0.4843 0.250 0.2493 0.00664 0.00123 -0.0473 0.6143 0.5079 0.750 0.3071 0.00662 0.00125 -0.0478 0.5964 0.5422 1.000 0.3355 0.00667 0.00127 -0.0480 0.5758 0.5584 1.250 0.3637 0.00673 0.00130 -0.0481 0.5490 0.5763 1.500 0.3917 0.00684 0.00135 -0.0482 0.5198 0.5917 1.750 0.4187 0.00706 0.00143 -0.0482 0.4734 0.6080 2.000 0.4455 0.00730 0.00156 -0.0482 0.4321 0.6249 2.500 0.5004 0.00756 0.00178 -0.0483 0.3868 0.6697 2.750 0.5278 0.00764 0.00189 -0.0483 0.3684 0.6988 3.000 0.5553 0.00771 0.00201 -0.0483 0.3529 0.7294 3.250 0.5826 0.00777 0.00213 -0.0483 0.3385 0.7609 3.500 0.6093 0.00782 0.00226 -0.0482 0.3239 0.8024 3.750 0.6346 0.00788 0.00241 -0.0477 0.3051 0.8509 4.000 0.6585 0.00801 0.00258 -0.0468 0.2829 0.8970 4.250 0.6816 0.00823 0.00277 -0.0458 0.2553 0.9343 4.500 0.7088 0.00846 0.00294 -0.0458 0.2333 0.9620 4.750 0.7395 0.00878 0.00315 -0.0466 0.2080 0.9804 5.000 0.7711 0.00909 0.00336 -0.0477 0.1858 0.9930 5.250 0.8019 0.00938 0.00357 -0.0487 0.1695 1.0000 5.500 0.8273 0.00963 0.00377 -0.0484 0.1562 1.0000 5.750 0.8527 0.00991 0.00399 -0.0481 0.1425 1.0000 6.000 0.8773 0.01027 0.00425 -0.0477 0.1236 1.0000 6.250 0.9013 0.01067 0.00454 -0.0472 0.1019 1.0000 6.500 0.9255 0.01106 0.00485 -0.0468 0.0875 1.0000 6.750 0.9504 0.01138 0.00513 -0.0464 0.0792 1.0000 7.000 0.9754 0.01169 0.00540 -0.0461 0.0730 1.0000 7.250 1.0009 0.01193 0.00566 -0.0458 0.0688 1.0000 7.500 1.0251 0.01229 0.00598 -0.0454 0.0607 1.0000 7.750 1.0471 0.01283 0.00638 -0.0446 0.0410 1.0000 8.000 1.0696 0.01331 0.00680 -0.0440 0.0323 1.0000 8.250 1.0927 0.01373 0.00721 -0.0434 0.0284 1.0000 8.500 1.1163 0.01408 0.00758 -0.0428 0.0261 1.0000 8.750 1.1396 0.01444 0.00796 -0.0423 0.0244 1.0000 9.000 1.1618 0.01487 0.00839 -0.0416 0.0223 1.0000 9.250 1.1841 0.01527 0.00881 -0.0409 0.0206 1.0000 9.500 1.2064 0.01566 0.00922 -0.0402 0.0190 1.0000 9.750 1.2273 0.01612 0.00968 -0.0393 0.0170 1.0000 10.000 1.2479 0.01658 0.01016 -0.0383 0.0156 1.0000 10.250 1.2678 0.01704 0.01064 -0.0373 0.0143 1.0000 10.500 1.2862 0.01757 0.01117 -0.0361 0.0129 1.0000 10.750 1.3025 0.01809 0.01171 -0.0344 0.0119 1.0000 11.000 1.3184 0.01862 0.01229 -0.0327 0.0112 1.0000 11.250 1.3337 0.01923 0.01293 -0.0311 0.0104 1.0000 11.500 1.3481 0.01992 0.01364 -0.0294 0.0097 1.0000 11.750 1.3623 0.02066 0.01442 -0.0279 0.0091 1.0000 12.000 1.3771 0.02137 0.01519 -0.0265 0.0088 1.0000 12.250 1.3913 0.02216 0.01603 -0.0251 0.0084 1.0000 12.500 1.4046 0.02303 0.01695 -0.0237 0.0080 1.0000 12.750 1.4172 0.02398 0.01795 -0.0224 0.0077 1.0000 13.000 1.4287 0.02503 0.01905 -0.0211 0.0073 1.0000 13.250 1.4391 0.02621 0.02028 -0.0197 0.0070 1.0000 13.500 1.4486 0.02749 0.02163 -0.0184 0.0067 1.0000 13.750 1.4592 0.02871 0.02292 -0.0174 0.0066 1.0000 14.000 1.4691 0.03004 0.02431 -0.0163 0.0064 1.0000 14.250 1.4780 0.03148 0.02583 -0.0154 0.0062 1.0000 14.500 1.4861 0.03303 0.02746 -0.0145 0.0060 1.0000 14.750 1.4931 0.03473 0.02922 -0.0137 0.0058 1.0000 15.000 1.4991 0.03658 0.03115 -0.0130 0.0056 1.0000 15.250 1.5037 0.03859 0.03323 -0.0123 0.0055 1.0000 15.500 1.5069 0.04079 0.03551 -0.0118 0.0054 1.0000 15.750 1.5088 0.04319 0.03799 -0.0113 0.0052 1.0000 16.000 1.5088 0.04583 0.04072 -0.0110 0.0051 1.0000 16.250 1.5066 0.04883 0.04381 -0.0108 0.0050 1.0000 16.500 1.5033 0.05208 0.04716 -0.0108 0.0049 1.0000 16.750 1.5016 0.05525 0.05043 -0.0110 0.0048 1.0000 17.000 1.4985 0.05866 0.05395 -0.0115 0.0048 1.0000 17.250 1.4940 0.06241 0.05782 -0.0121 0.0047 1.0000 17.500 1.4879 0.06649 0.06201 -0.0130 0.0047 1.0000 17.750 1.4800 0.07098 0.06661 -0.0142 0.0046 1.0000 18.000 1.4701 0.07590 0.07165 -0.0157 0.0046 1.0000 18.250 1.4585 0.08124 0.07711 -0.0175 0.0046 1.0000 18.500 1.4453 0.08700 0.08300 -0.0197 0.0045 1.0000 18.750 1.4303 0.09314 0.08926 -0.0221 0.0045 1.0000 19.000 1.4132 0.09971 0.09596 -0.0248 0.0045 1.0000 19.250 1.3946 0.10667 0.10306 -0.0277 0.0044 1.0000