XFOIL Version 6.96 Calculated polar for: GOE 394 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3871 0.11941 0.11763 -0.0044 0.8899 0.0131 -9.750 -0.3834 0.11617 0.11420 -0.0055 0.8446 0.0132 -9.500 -0.3777 0.11279 0.11071 -0.0070 0.8191 0.0132 -9.250 -0.3743 0.10849 0.10634 -0.0082 0.8045 0.0134 -9.000 -0.3649 0.10611 0.10390 -0.0087 0.7944 0.0136 -8.750 -0.3556 0.10370 0.10145 -0.0097 0.7870 0.0138 -8.500 -0.3463 0.10118 0.09891 -0.0110 0.7811 0.0142 -8.250 -0.3373 0.09850 0.09620 -0.0124 0.7762 0.0146 -8.000 -0.3283 0.09563 0.09331 -0.0141 0.7723 0.0153 -7.750 -0.3210 0.09155 0.08923 -0.0183 0.7685 0.0167 -7.500 -0.3118 0.08795 0.08562 -0.0219 0.7650 0.0168 -7.250 -0.2980 0.08388 0.08153 -0.0263 0.7616 0.0168 -7.000 -0.2867 0.07808 0.07570 -0.0318 0.7583 0.0171 -6.750 -0.2706 0.07610 0.07371 -0.0329 0.7548 0.0174 -6.500 -0.2523 0.07390 0.07149 -0.0353 0.7512 0.0179 -6.250 -0.2322 0.07128 0.06884 -0.0387 0.7479 0.0186 -6.000 -0.1997 0.06636 0.06385 -0.0483 0.7447 0.0212 -5.750 -0.1710 0.06149 0.05894 -0.0554 0.7423 0.0213 -4.500 0.0242 0.01712 0.01305 -0.1059 0.7315 0.0264 -4.250 0.0531 0.01554 0.01115 -0.1067 0.7289 0.0269 -4.000 0.0819 0.01320 0.00836 -0.1076 0.7268 0.0275 -3.750 0.1101 0.01152 0.00640 -0.1081 0.7246 0.0286 -3.500 0.1384 0.01093 0.00573 -0.1082 0.7224 0.0293 -3.250 0.1668 0.01038 0.00507 -0.1082 0.7200 0.0298 -3.000 0.1951 0.00991 0.00448 -0.1082 0.7174 0.0302 -2.750 0.2234 0.00952 0.00397 -0.1082 0.7145 0.0306 -2.500 0.2519 0.00915 0.00353 -0.1081 0.7119 0.0311 -2.250 0.2804 0.00880 0.00313 -0.1081 0.7092 0.0317 -2.000 0.3089 0.00854 0.00283 -0.1081 0.7065 0.0326 -1.750 0.3373 0.00830 0.00254 -0.1080 0.7038 0.0333 -1.500 0.3657 0.00812 0.00230 -0.1079 0.7008 0.0339 -1.250 0.3940 0.00799 0.00212 -0.1078 0.6979 0.0343 -1.000 0.4226 0.00777 0.00189 -0.1078 0.6951 0.0349 -0.750 0.4511 0.00756 0.00166 -0.1077 0.6915 0.0362 -0.500 0.4795 0.00742 0.00150 -0.1076 0.6880 0.0381 -0.250 0.5078 0.00733 0.00139 -0.1075 0.6841 0.0408 0.000 0.5363 0.00718 0.00129 -0.1075 0.6801 0.0512 0.250 0.5647 0.00717 0.00143 -0.1074 0.6754 0.0823 0.500 0.5929 0.00730 0.00155 -0.1073 0.6704 0.0877 0.750 0.6212 0.00725 0.00152 -0.1072 0.6648 0.0912 1.000 0.6496 0.00724 0.00154 -0.1071 0.6579 0.0943 1.250 0.6778 0.00723 0.00153 -0.1071 0.6500 0.0969 1.500 0.7059 0.00724 0.00152 -0.1070 0.6361 0.0995 1.750 0.7338 0.00727 0.00150 -0.1068 0.6109 0.1008 2.000 0.7604 0.00740 0.00142 -0.1066 0.5555 0.1034 2.250 0.7869 0.00764 0.00150 -0.1063 0.5151 0.1059 2.500 0.8138 0.00785 0.00161 -0.1062 0.4896 0.1087 2.750 0.8410 0.00800 0.00170 -0.1060 0.4710 0.1110 3.000 0.8683 0.00813 0.00178 -0.1059 0.4549 0.1125 3.250 0.8956 0.00825 0.00187 -0.1058 0.4407 0.1138 3.500 0.9230 0.00836 0.00195 -0.1057 0.4295 0.1156 3.750 0.9503 0.00845 0.00204 -0.1056 0.4176 0.1181 4.000 0.9777 0.00855 0.00213 -0.1054 0.4069 0.1204 4.250 1.0049 0.00866 0.00225 -0.1053 0.3974 0.1228 4.750 1.0591 0.00894 0.00250 -0.1050 0.3731 0.1288 5.000 1.0860 0.00906 0.00265 -0.1049 0.3604 0.1422 5.250 1.1109 0.00798 0.00304 -0.1048 0.3445 1.0000 5.500 1.1370 0.00827 0.00323 -0.1045 0.3209 1.0000 5.750 1.1625 0.00865 0.00346 -0.1042 0.2904 1.0000 6.000 1.1870 0.00915 0.00376 -0.1038 0.2521 1.0000 6.250 1.2094 0.00996 0.00423 -0.1032 0.1913 1.0000 6.500 1.2306 0.01091 0.00484 -0.1024 0.1320 1.0000 6.750 1.2546 0.01143 0.00526 -0.1019 0.1122 1.0000 7.000 1.2791 0.01185 0.00562 -0.1015 0.0997 1.0000 7.250 1.3034 0.01228 0.00599 -0.1010 0.0858 1.0000 7.500 1.3262 0.01290 0.00646 -0.1004 0.0608 1.0000 7.750 1.3458 0.01394 0.00725 -0.0994 0.0275 1.0000 8.000 1.3680 0.01458 0.00786 -0.0986 0.0205 1.0000 8.250 1.3903 0.01518 0.00848 -0.0978 0.0174 1.0000 8.500 1.4132 0.01567 0.00900 -0.0971 0.0159 1.0000 8.750 1.4345 0.01632 0.00968 -0.0962 0.0142 1.0000 9.000 1.4549 0.01706 0.01048 -0.0952 0.0132 1.0000 9.250 1.4764 0.01760 0.01107 -0.0943 0.0126 1.0000 9.500 1.4970 0.01821 0.01173 -0.0934 0.0119 1.0000 9.750 1.5166 0.01888 0.01245 -0.0923 0.0113 1.0000 10.000 1.5341 0.01972 0.01334 -0.0910 0.0107 1.0000 10.250 1.5433 0.02126 0.01501 -0.0885 0.0099 1.0000 10.500 1.5620 0.02183 0.01562 -0.0874 0.0097 1.0000 10.750 1.5782 0.02255 0.01640 -0.0859 0.0094 1.0000 11.000 1.5898 0.02340 0.01733 -0.0837 0.0091 1.0000 11.250 1.5995 0.02437 0.01838 -0.0814 0.0088 1.0000 11.500 1.6086 0.02543 0.01952 -0.0793 0.0085 1.0000 11.750 1.6168 0.02663 0.02078 -0.0773 0.0082 1.0000 12.000 1.6240 0.02798 0.02221 -0.0754 0.0080 1.0000 12.250 1.6288 0.02964 0.02394 -0.0736 0.0078 1.0000 12.500 1.6287 0.03185 0.02625 -0.0717 0.0076 1.0000 12.750 1.6211 0.03493 0.02947 -0.0696 0.0073 1.0000 13.000 1.6143 0.03810 0.03278 -0.0679 0.0072 1.0000 13.250 1.6194 0.04012 0.03491 -0.0670 0.0071 1.0000 13.500 1.6231 0.04232 0.03721 -0.0661 0.0070 1.0000 13.750 1.6249 0.04476 0.03975 -0.0653 0.0069 1.0000 14.000 1.6246 0.04748 0.04257 -0.0645 0.0068 1.0000 14.250 1.6228 0.05039 0.04560 -0.0638 0.0067 1.0000 14.500 1.6204 0.05345 0.04877 -0.0632 0.0066 1.0000 14.750 1.6172 0.05670 0.05213 -0.0628 0.0065 1.0000 15.000 1.6135 0.06009 0.05563 -0.0627 0.0064 1.0000 15.250 1.6097 0.06371 0.05936 -0.0628 0.0063 1.0000 15.500 1.6051 0.06761 0.06337 -0.0633 0.0062 1.0000 15.750 1.5995 0.07180 0.06768 -0.0640 0.0061 1.0000 16.000 1.5940 0.07614 0.07213 -0.0650 0.0060 1.0000 16.250 1.5869 0.08089 0.07699 -0.0662 0.0059 1.0000 16.500 1.5789 0.08588 0.08210 -0.0676 0.0058 1.0000 16.750 1.5704 0.09102 0.08736 -0.0692 0.0058 1.0000 17.000 1.5609 0.09640 0.09285 -0.0710 0.0057 1.0000 17.250 1.5502 0.10208 0.09864 -0.0730 0.0057 1.0000 17.500 1.5394 0.10784 0.10451 -0.0752 0.0056 1.0000 17.750 1.5278 0.11378 0.11056 -0.0775 0.0056 1.0000 18.000 1.5153 0.12001 0.11691 -0.0801 0.0055 1.0000 18.250 1.5031 0.12633 0.12334 -0.0829 0.0055 1.0000 18.500 1.4912 0.13274 0.12986 -0.0859 0.0055 1.0000 18.750 1.4791 0.13926 0.13649 -0.0891 0.0054 1.0000 19.000 1.4668 0.14602 0.14336 -0.0926 0.0054 1.0000 19.250 1.4547 0.15295 0.15040 -0.0964 0.0054 1.0000