XFOIL Version 6.96 Calculated polar for: GOE 655 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 ------ -------- --------- --------- -------- -------- -------- -16.500 -1.0022 0.05271 0.04977 -0.0860 1.0000 0.0127 -16.250 -1.0624 0.03957 0.03635 -0.0965 1.0000 0.0125 -16.000 -1.0891 0.03246 0.02903 -0.1029 1.0000 0.0126 -15.750 -1.1086 0.02945 0.02590 -0.1024 1.0000 0.0126 -15.500 -1.1289 0.02800 0.02435 -0.0977 1.0000 0.0126 -15.250 -1.1145 0.02655 0.02282 -0.0982 0.9977 0.0130 -15.000 -1.0926 0.02520 0.02137 -0.0994 0.9946 0.0134 -14.750 -1.0721 0.02407 0.02015 -0.0998 0.9914 0.0138 -14.500 -1.0493 0.02305 0.01905 -0.1003 0.9881 0.0142 -14.250 -1.0241 0.02209 0.01799 -0.1012 0.9855 0.0146 -14.000 -0.9972 0.02122 0.01708 -0.1021 0.9837 0.0151 -13.750 -0.9750 0.02053 0.01634 -0.1018 0.9799 0.0156 -13.500 -0.9499 0.01986 0.01561 -0.1021 0.9769 0.0161 -13.250 -0.9222 0.01924 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0.6064 0.00884 0.00224 -0.0782 0.3193 0.4909 1.750 0.6316 0.00883 0.00231 -0.0777 0.3157 0.5275 2.000 0.6566 0.00877 0.00238 -0.0770 0.3126 0.5774 2.250 0.6795 0.00864 0.00247 -0.0760 0.3090 0.6626 2.500 0.6998 0.00849 0.00258 -0.0743 0.3039 0.7640 2.750 0.7190 0.00831 0.00269 -0.0723 0.2996 0.8703 3.000 0.7985 0.00840 0.00292 -0.0836 0.2950 0.9726 3.250 0.8394 0.00855 0.00303 -0.0864 0.2912 0.9881 3.500 0.8707 0.00870 0.00315 -0.0872 0.2875 0.9981 3.750 0.9004 0.00885 0.00326 -0.0877 0.2837 1.0000 4.000 0.9240 0.00895 0.00335 -0.0868 0.2807 1.0000 4.250 0.9473 0.00907 0.00345 -0.0858 0.2769 1.0000 4.500 0.9703 0.00921 0.00356 -0.0848 0.2728 1.0000 4.750 0.9930 0.00936 0.00369 -0.0838 0.2686 1.0000 5.000 1.0166 0.00948 0.00380 -0.0829 0.2653 1.0000 5.250 1.0395 0.00962 0.00392 -0.0819 0.2596 1.0000 5.500 1.0615 0.00981 0.00407 -0.0808 0.2536 1.0000 5.750 1.0844 0.00995 0.00421 -0.0798 0.2484 1.0000 6.000 1.1061 0.01016 0.00436 -0.0787 0.2408 1.0000 6.250 1.1279 0.01035 0.00453 -0.0775 0.2328 1.0000 6.500 1.1484 0.01061 0.00473 -0.0762 0.2217 1.0000 6.750 1.1668 0.01096 0.00498 -0.0745 0.2045 1.0000 7.000 1.1844 0.01134 0.00528 -0.0727 0.1896 1.0000 7.250 1.2025 0.01166 0.00555 -0.0709 0.1806 1.0000 7.500 1.2196 0.01196 0.00582 -0.0690 0.1741 1.0000 7.750 1.2368 0.01225 0.00609 -0.0670 0.1687 1.0000 8.000 1.2536 0.01256 0.00638 -0.0651 0.1628 1.0000 8.250 1.2706 0.01290 0.00669 -0.0632 0.1580 1.0000 8.500 1.2889 0.01318 0.00698 -0.0616 0.1545 1.0000 8.750 1.3080 0.01344 0.00726 -0.0602 0.1517 1.0000 9.000 1.3269 0.01372 0.00755 -0.0588 0.1495 1.0000 9.250 1.3444 0.01408 0.00790 -0.0572 0.1458 1.0000 9.500 1.3620 0.01444 0.00827 -0.0557 0.1428 1.0000 9.750 1.3803 0.01478 0.00863 -0.0543 0.1404 1.0000 10.000 1.3992 0.01509 0.00896 -0.0530 0.1380 1.0000 10.250 1.4171 0.01546 0.00935 -0.0517 0.1352 1.0000 10.500 1.4335 0.01591 0.00979 -0.0502 0.1310 1.0000 10.750 1.4495 0.01640 0.01029 -0.0486 0.1274 1.0000 11.000 1.4672 0.01681 0.01073 -0.0474 0.1239 1.0000 11.250 1.4817 0.01740 0.01129 -0.0458 0.1178 1.0000 11.500 1.4950 0.01808 0.01195 -0.0442 0.1096 1.0000 11.750 1.5045 0.01900 0.01280 -0.0421 0.0979 1.0000 12.000 1.4934 0.02120 0.01478 -0.0381 0.0661 1.0000 12.250 1.4678 0.02463 0.01801 -0.0334 0.0296 1.0000 12.500 1.4644 0.02680 0.02016 -0.0312 0.0177 1.0000 12.750 1.4709 0.02832 0.02172 -0.0300 0.0154 1.0000 13.000 1.4773 0.02990 0.02335 -0.0290 0.0138 1.0000 13.250 1.4850 0.03145 0.02495 -0.0281 0.0130 1.0000 13.500 1.4917 0.03313 0.02669 -0.0273 0.0124 1.0000 13.750 1.4958 0.03510 0.02872 -0.0266 0.0115 1.0000 14.000 1.5001 0.03712 0.03080 -0.0260 0.0111 1.0000 14.250 1.5049 0.03913 0.03288 -0.0255 0.0107 1.0000 14.500 1.5085 0.04135 0.03516 -0.0251 0.0104 1.0000 14.750 1.5107 0.04373 0.03761 -0.0248 0.0101 1.0000 15.000 1.5108 0.04641 0.04037 -0.0246 0.0097 1.0000 15.250 1.5099 0.04930 0.04334 -0.0246 0.0094 1.0000 15.500 1.5073 0.05246 0.04657 -0.0247 0.0091 1.0000 15.750 1.5034 0.05583 0.05002 -0.0249 0.0087 1.0000 16.000 1.4993 0.05934 0.05363 -0.0252 0.0086 1.0000 16.250 1.4946 0.06301 0.05739 -0.0257 0.0085 1.0000 16.500 1.4894 0.06676 0.06123 -0.0263 0.0082 1.0000 16.750 1.4825 0.07079 0.06534 -0.0270 0.0081 1.0000 17.000 1.4731 0.07524 0.06990 -0.0279 0.0081 1.0000 17.250 1.4641 0.07968 0.07443 -0.0289 0.0078 1.0000 17.500 1.4532 0.08439 0.07924 -0.0299 0.0077 1.0000 17.750 1.4421 0.08920 0.08414 -0.0311 0.0076 1.0000 18.000 1.4294 0.09432 0.08936 -0.0324 0.0075 1.0000 18.250 1.4180 0.09926 0.09439 -0.0337 0.0073 1.0000 18.500 1.4057 0.10436 0.09959 -0.0352 0.0073 1.0000 18.750 1.3928 0.10964 0.10495 -0.0368 0.0071 1.0000