XFOIL Version 6.96 Calculated polar for: GOE 584 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -1.0965 0.03224 0.02933 -0.1052 1.0000 0.0198 -15.500 -1.1128 0.03018 0.02715 -0.1017 1.0000 0.0201 -15.250 -1.1150 0.02851 0.02535 -0.0992 1.0000 0.0204 -15.000 -1.1126 0.02712 0.02386 -0.0968 1.0000 0.0207 -14.750 -1.1071 0.02593 0.02255 -0.0944 1.0000 0.0211 -14.500 -1.0995 0.02493 0.02144 -0.0920 1.0000 0.0215 -14.250 -1.0976 0.02365 0.02008 -0.0888 1.0000 0.0221 -14.000 -1.0699 0.02254 0.01892 -0.0902 0.9983 0.0229 -13.750 -1.0382 0.02165 0.01796 -0.0919 0.9957 0.0237 -13.500 -1.0070 0.02080 0.01701 -0.0934 0.9927 0.0245 -13.250 -0.9773 0.02000 0.01608 -0.0945 0.9886 0.0251 -13.000 -0.9464 0.01912 0.01518 -0.0960 0.9847 0.0262 -12.750 -0.9135 0.01866 0.01470 -0.0973 0.9810 0.0271 -12.500 -0.8822 0.01823 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0.2006 0.00905 0.00269 -0.0904 0.6369 0.0583 -2.250 0.2275 0.00891 0.00252 -0.0901 0.6311 0.0590 -2.000 0.2538 0.00867 0.00225 -0.0896 0.6246 0.0607 -1.750 0.2803 0.00858 0.00213 -0.0892 0.6178 0.0623 -1.500 0.3078 0.00847 0.00202 -0.0890 0.6117 0.0635 -1.250 0.3349 0.00841 0.00193 -0.0887 0.6055 0.0650 -1.000 0.3620 0.00837 0.00187 -0.0884 0.5998 0.0664 -0.750 0.3897 0.00831 0.00180 -0.0882 0.5943 0.0676 -0.500 0.4165 0.00823 0.00170 -0.0879 0.5885 0.0706 -0.250 0.4435 0.00818 0.00166 -0.0876 0.5831 0.0746 0.000 0.4710 0.00812 0.00161 -0.0874 0.5776 0.0806 0.250 0.4972 0.00798 0.00158 -0.0870 0.5719 0.1147 0.500 0.5228 0.00778 0.00160 -0.0865 0.5667 0.1930 0.750 0.5494 0.00764 0.00162 -0.0862 0.5610 0.2436 1.000 0.5747 0.00747 0.00165 -0.0857 0.5553 0.3269 1.250 0.5991 0.00721 0.00169 -0.0851 0.5498 0.4445 1.500 0.6172 0.00654 0.00177 -0.0832 0.5446 0.7126 1.750 0.6756 0.00612 0.00196 -0.0895 0.5374 0.9697 2.000 0.7243 0.00622 0.00203 -0.0940 0.5312 0.9887 2.250 0.7705 0.00632 0.00208 -0.0979 0.5241 0.9970 2.500 0.8105 0.00641 0.00212 -0.1005 0.5174 1.0000 2.750 0.8349 0.00647 0.00217 -0.0997 0.5109 1.0000 3.000 0.8584 0.00658 0.00223 -0.0988 0.5041 1.0000 3.250 0.8827 0.00665 0.00228 -0.0980 0.4964 1.0000 3.750 0.9299 0.00687 0.00243 -0.0961 0.4770 1.0000 4.000 0.9531 0.00701 0.00251 -0.0952 0.4657 1.0000 4.250 0.9759 0.00717 0.00261 -0.0941 0.4544 1.0000 4.500 0.9999 0.00728 0.00271 -0.0933 0.4448 1.0000 4.750 1.0230 0.00744 0.00283 -0.0923 0.4344 1.0000 5.000 1.0455 0.00763 0.00296 -0.0912 0.4223 1.0000 5.250 1.0681 0.00781 0.00309 -0.0902 0.4086 1.0000 5.500 1.0907 0.00800 0.00324 -0.0891 0.3958 1.0000 5.750 1.1128 0.00821 0.00340 -0.0880 0.3826 1.0000 6.000 1.1345 0.00845 0.00358 -0.0869 0.3694 1.0000 6.250 1.1557 0.00870 0.00378 -0.0856 0.3556 1.0000 6.500 1.1765 0.00898 0.00400 -0.0843 0.3415 1.0000 6.750 1.1967 0.00927 0.00422 -0.0829 0.3271 1.0000 7.000 1.2164 0.00959 0.00447 -0.0814 0.3114 1.0000 7.500 1.2556 0.01021 0.00498 -0.0785 0.2833 1.0000 7.750 1.2750 0.01052 0.00524 -0.0770 0.2702 1.0000 8.000 1.2935 0.01085 0.00552 -0.0754 0.2571 1.0000 8.250 1.3111 0.01121 0.00583 -0.0736 0.2435 1.0000 8.500 1.3272 0.01161 0.00616 -0.0716 0.2283 1.0000 8.750 1.3403 0.01203 0.00651 -0.0690 0.2141 1.0000 9.000 1.3514 0.01248 0.00690 -0.0661 0.1990 1.0000 9.250 1.3629 0.01296 0.00731 -0.0633 0.1851 1.0000 9.500 1.3744 0.01348 0.00778 -0.0607 0.1716 1.0000 9.750 1.3851 0.01408 0.00831 -0.0581 0.1578 1.0000 10.000 1.3954 0.01474 0.00890 -0.0555 0.1445 1.0000 10.250 1.4061 0.01542 0.00954 -0.0532 0.1339 1.0000 10.500 1.4183 0.01607 0.01016 -0.0512 0.1253 1.0000 10.750 1.4305 0.01677 0.01085 -0.0493 0.1182 1.0000 11.000 1.4430 0.01750 0.01157 -0.0476 0.1123 1.0000 11.250 1.4543 0.01833 0.01240 -0.0458 0.1048 1.0000 11.500 1.4647 0.01927 0.01331 -0.0441 0.0979 1.0000 11.750 1.4767 0.02017 0.01421 -0.0427 0.0914 1.0000 12.000 1.4855 0.02132 0.01533 -0.0411 0.0830 1.0000 12.250 1.4911 0.02275 0.01670 -0.0394 0.0704 1.0000 12.500 1.4867 0.02499 0.01879 -0.0372 0.0496 1.0000 12.750 1.4800 0.02751 0.02122 -0.0350 0.0345 1.0000 13.000 1.4824 0.02942 0.02314 -0.0336 0.0298 1.0000 13.250 1.4861 0.03128 0.02503 -0.0324 0.0275 1.0000 13.500 1.4915 0.03303 0.02683 -0.0314 0.0259 1.0000 13.750 1.4968 0.03483 0.02869 -0.0305 0.0247 1.0000 14.000 1.4996 0.03690 0.03080 -0.0296 0.0235 1.0000 14.250 1.5006 0.03919 0.03315 -0.0287 0.0224 1.0000 14.500 1.5067 0.04107 0.03510 -0.0281 0.0219 1.0000 14.750 1.5115 0.04311 0.03720 -0.0276 0.0211 1.0000 15.000 1.5147 0.04534 0.03948 -0.0271 0.0204 1.0000 15.250 1.5154 0.04788 0.04208 -0.0266 0.0198 1.0000 15.500 1.5128 0.05084 0.04512 -0.0262 0.0191 1.0000 15.750 1.5127 0.05359 0.04795 -0.0260 0.0187 1.0000 16.000 1.5155 0.05606 0.05048 -0.0258 0.0183 1.0000 16.250 1.5160 0.05883 0.05333 -0.0257 0.0180 1.0000 16.500 1.5165 0.06163 0.05620 -0.0257 0.0175 1.0000 16.750 1.5156 0.06463 0.05927 -0.0258 0.0171 1.0000 17.000 1.5124 0.06796 0.06267 -0.0259 0.0167 1.0000 17.250 1.5078 0.07152 0.06630 -0.0262 0.0165 1.0000 17.500 1.4991 0.07567 0.07054 -0.0267 0.0161 1.0000 17.750 1.4850 0.08060 0.07557 -0.0273 0.0157 1.0000 18.000 1.4815 0.08417 0.07923 -0.0279 0.0156 1.0000