XFOIL Version 6.94 Calculated polar for: GOE 693 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3773 0.00753 0.00255 -0.0839 0.7057 0.7832 0.500 0.4559 0.00737 0.00269 -0.0878 0.6929 0.9856 1.000 0.5354 0.00751 0.00267 -0.0930 0.6789 1.0000 1.500 0.5871 0.00760 0.00269 -0.0921 0.6648 1.0000 2.000 0.6388 0.00772 0.00273 -0.0911 0.6490 1.0000 2.500 0.6900 0.00786 0.00278 -0.0901 0.6287 1.0000 3.000 0.7414 0.00802 0.00288 -0.0891 0.6074 1.0000 3.500 0.7898 0.00828 0.00295 -0.0875 0.5601 1.0000 4.000 0.8365 0.00877 0.00315 -0.0856 0.4938 1.0000 4.500 0.8803 0.00957 0.00357 -0.0835 0.4183 1.0000 5.000 0.9198 0.01076 0.00425 -0.0808 0.3314 1.0000 5.500 0.9645 0.01159 0.00480 -0.0790 0.2773 1.0000 6.000 0.9962 0.01337 0.00584 -0.0753 0.1578 1.0000 6.500 1.0200 0.01565 0.00730 -0.0705 0.0317 1.0000 7.000 1.0570 0.01686 0.00842 -0.0674 0.0047 1.0000 7.500 1.0977 0.01769 0.00933 -0.0649 0.0039 1.0000 8.000 1.1337 0.01859 0.01035 -0.0616 0.0036 1.0000 8.500 1.1672 0.01967 0.01158 -0.0581 0.0035 1.0000 9.000 1.1976 0.02104 0.01312 -0.0544 0.0035 1.0000 9.500 1.2245 0.02273 0.01504 -0.0506 0.0035 1.0000 10.000 1.2477 0.02478 0.01728 -0.0467 0.0035 1.0000 10.500 1.2672 0.02723 0.01991 -0.0429 0.0036 1.0000 11.000 1.2828 0.03015 0.02302 -0.0394 0.0037 1.0000 11.500 1.2950 0.03358 0.02665 -0.0362 0.0038 1.0000 12.000 1.3036 0.03758 0.03086 -0.0335 0.0040 1.0000 12.500 1.3087 0.04218 0.03571 -0.0313 0.0042 1.0000 13.000 1.3101 0.04741 0.04118 -0.0294 0.0044 1.0000 13.500 1.3074 0.05338 0.04741 -0.0280 0.0047 1.0000 14.000 1.3018 0.05997 0.05427 -0.0270 0.0050 1.0000 14.500 1.2934 0.06720 0.06180 -0.0263 0.0054 1.0000 15.000 1.2831 0.07501 0.06991 -0.0262 0.0058 1.0000 15.500 1.2690 0.08374 0.07895 -0.0267 0.0062 1.0000 16.000 1.2477 0.09358 0.08912 -0.0271 0.0068 1.0000 16.500 1.2497 0.10111 0.09681 -0.0301 0.0071 1.0000 17.000 1.2444 0.11019 0.10614 -0.0340 0.0075 1.0000 17.500 1.2175 0.12361 0.12008 -0.0392 0.0088 1.0000 18.000 1.1841 0.13950 0.13636 -0.0480 0.0093 1.0000 18.500 1.1501 0.15711 0.15431 -0.0593 0.0096 1.0000 19.000 1.1217 0.17519 0.17265 -0.0716 0.0094 1.0000 19.500 1.0961 0.19448 0.19212 -0.0846 0.0088 1.0000