XFOIL Version 6.96 Calculated polar for: GOE 504 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.6200 0.11268 0.11040 -0.0710 0.9999 0.0086 -18.250 -0.6538 0.10213 0.09970 -0.0774 0.9995 0.0088 -18.000 -0.6806 0.09303 0.09046 -0.0833 0.9990 0.0087 -17.750 -0.6979 0.08563 0.08297 -0.0885 0.9983 0.0088 -17.500 -0.7136 0.07868 0.07590 -0.0936 0.9972 0.0088 -17.250 -0.7335 0.07163 0.06874 -0.0986 0.9939 0.0089 -17.000 -0.7543 0.06497 0.06197 -0.1033 0.9916 0.0089 -16.750 -0.7711 0.05880 0.05570 -0.1080 0.9888 0.0090 -16.500 -0.7856 0.05264 0.04942 -0.1132 0.9857 0.0091 -16.250 -0.8012 0.04636 0.04301 -0.1185 0.9817 0.0091 -16.000 -0.8084 0.04088 0.03740 -0.1235 0.9767 0.0092 -15.750 -0.8049 0.03592 0.03230 -0.1295 0.9732 0.0094 -15.500 -0.7998 0.03161 0.02784 -0.1350 0.9673 0.0093 -15.250 -0.7841 0.02839 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0.5026 0.1992 -0.750 0.4299 0.00894 0.00217 -0.0946 0.4981 0.2230 -0.500 0.4530 0.00890 0.00218 -0.0937 0.4932 0.2433 -0.250 0.4744 0.00891 0.00220 -0.0924 0.4878 0.2568 0.000 0.4963 0.00891 0.00221 -0.0913 0.4827 0.2659 0.250 0.5187 0.00892 0.00222 -0.0902 0.4778 0.2746 0.500 0.5398 0.00895 0.00225 -0.0889 0.4724 0.2851 0.750 0.5619 0.00898 0.00228 -0.0878 0.4679 0.2943 1.000 0.5840 0.00900 0.00232 -0.0867 0.4619 0.3027 1.250 0.6049 0.00906 0.00237 -0.0855 0.4564 0.3127 1.500 0.6260 0.00907 0.00244 -0.0842 0.4512 0.3378 1.750 0.6476 0.00910 0.00252 -0.0831 0.4455 0.3582 2.000 0.6670 0.00917 0.00262 -0.0815 0.4390 0.3814 2.250 0.6887 0.00920 0.00271 -0.0805 0.4341 0.4039 2.500 0.7093 0.00924 0.00281 -0.0792 0.4283 0.4326 2.750 0.7281 0.00929 0.00293 -0.0776 0.4225 0.4709 3.000 0.7477 0.00928 0.00305 -0.0761 0.4167 0.5218 3.250 0.7655 0.00928 0.00319 -0.0743 0.4111 0.5803 3.500 0.7806 0.00922 0.00335 -0.0719 0.4056 0.6632 3.750 0.7943 0.00912 0.00350 -0.0692 0.4009 0.7532 4.000 0.8058 0.00906 0.00369 -0.0659 0.3946 0.8403 4.250 0.9131 0.00920 0.00405 -0.0837 0.3853 0.9536 4.500 0.9771 0.00950 0.00430 -0.0921 0.3773 0.9768 4.750 1.0098 0.00970 0.00448 -0.0935 0.3718 0.9880 5.000 1.0348 0.00998 0.00472 -0.0934 0.3650 0.9989 5.250 1.0597 0.01021 0.00492 -0.0933 0.3594 1.0000 5.500 1.0759 0.01040 0.00510 -0.0913 0.3532 1.0000 5.750 1.0916 0.01064 0.00531 -0.0892 0.3475 1.0000 6.000 1.1090 0.01086 0.00552 -0.0875 0.3429 1.0000 6.250 1.1260 0.01111 0.00575 -0.0858 0.3364 1.0000 6.500 1.1414 0.01144 0.00604 -0.0838 0.3285 1.0000 6.750 1.1552 0.01184 0.00639 -0.0817 0.3169 1.0000 7.000 1.1731 0.01213 0.00667 -0.0803 0.3121 1.0000 7.250 1.1879 0.01255 0.00705 -0.0784 0.3022 1.0000 7.500 1.2041 0.01295 0.00742 -0.0768 0.2944 1.0000 7.750 1.2173 0.01348 0.00789 -0.0748 0.2832 1.0000 8.000 1.2291 0.01409 0.00844 -0.0727 0.2702 1.0000 8.250 1.2458 0.01453 0.00887 -0.0713 0.2635 1.0000 8.500 1.2582 0.01517 0.00947 -0.0695 0.2533 1.0000 8.750 1.2703 0.01586 0.01011 -0.0676 0.2421 1.0000 9.000 1.2806 0.01667 0.01086 -0.0656 0.2290 1.0000 9.250 1.2882 0.01766 0.01177 -0.0634 0.2139 1.0000 9.500 1.2965 0.01866 0.01270 -0.0613 0.2006 1.0000 9.750 1.2979 0.02009 0.01403 -0.0586 0.1810 1.0000 10.000 1.2865 0.02239 0.01613 -0.0548 0.1461 1.0000 10.250 1.2597 0.02592 0.01939 -0.0499 0.0991 1.0000 10.500 1.2326 0.02983 0.02310 -0.0458 0.0510 1.0000 10.750 1.2195 0.03298 0.02616 -0.0431 0.0169 1.0000 11.000 1.2272 0.03455 0.02776 -0.0422 0.0140 1.0000 11.250 1.2365 0.03602 0.02926 -0.0414 0.0127 1.0000 11.500 1.2447 0.03762 0.03090 -0.0406 0.0118 1.0000 11.750 1.2521 0.03932 0.03265 -0.0399 0.0110 1.0000 12.000 1.2599 0.04101 0.03437 -0.0392 0.0107 1.0000 12.250 1.2678 0.04272 0.03613 -0.0386 0.0101 1.0000 12.500 1.2748 0.04455 0.03800 -0.0380 0.0097 1.0000 12.750 1.2809 0.04648 0.03998 -0.0374 0.0092 1.0000 13.000 1.2857 0.04858 0.04212 -0.0369 0.0087 1.0000 13.250 1.2890 0.05087 0.04447 -0.0363 0.0083 1.0000 13.500 1.2932 0.05309 0.04674 -0.0359 0.0081 1.0000 13.750 1.2989 0.05519 0.04889 -0.0355 0.0078 1.0000 14.000 1.3025 0.05754 0.05130 -0.0352 0.0075 1.0000 14.250 1.3053 0.06002 0.05383 -0.0349 0.0074 1.0000 14.500 1.3081 0.06251 0.05638 -0.0347 0.0071 1.0000 14.750 1.3095 0.06519 0.05913 -0.0345 0.0069 1.0000 15.000 1.3111 0.06788 0.06187 -0.0343 0.0068 1.0000 15.250 1.3116 0.07073 0.06477 -0.0343 0.0065 1.0000 15.500 1.3111 0.07375 0.06786 -0.0342 0.0064 1.0000 15.750 1.3089 0.07699 0.07117 -0.0343 0.0063 1.0000 16.000 1.3074 0.08016 0.07441 -0.0343 0.0060 1.0000 16.250 1.3061 0.08336 0.07768 -0.0345 0.0060 1.0000 16.500 1.3045 0.08665 0.08103 -0.0347 0.0058 1.0000 16.750 1.3021 0.09006 0.08452 -0.0350 0.0058 1.0000 17.000 1.2990 0.09357 0.08811 -0.0354 0.0056 1.0000 17.250 1.2962 0.09708 0.09169 -0.0358 0.0055 1.0000 17.500 1.2940 0.10051 0.09518 -0.0363 0.0053 1.0000 17.750 1.2905 0.10419 0.09893 -0.0369 0.0053 1.0000 18.000 1.2877 0.10780 0.10261 -0.0375 0.0051 1.0000 18.250 1.2842 0.11152 0.10639 -0.0383 0.0050 1.0000 18.500 1.2802 0.11532 0.11026 -0.0391 0.0049 1.0000 18.750 1.2752 0.11928 0.11429 -0.0400 0.0049 1.0000 19.000 1.2735 0.12279 0.11786 -0.0409 0.0048 1.0000