XFOIL Version 6.96 Calculated polar for: GOE 255 (MVA CA.6) 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.7588 0.08449 0.08127 -0.0780 0.9851 0.0063 -17.000 -0.7744 0.07822 0.07490 -0.0817 0.9805 0.0064 -16.750 -0.7904 0.07218 0.06875 -0.0850 0.9753 0.0064 -16.500 -0.8061 0.06647 0.06293 -0.0881 0.9702 0.0064 -16.250 -0.8231 0.06112 0.05747 -0.0907 0.9637 0.0064 -16.000 -0.8400 0.05604 0.05228 -0.0931 0.9579 0.0064 -15.750 -0.8550 0.05123 0.04736 -0.0955 0.9513 0.0065 -15.500 -0.8686 0.04672 0.04274 -0.0976 0.9442 0.0065 -15.250 -0.8794 0.04239 0.03830 -0.0998 0.9335 0.0065 -15.000 -0.8864 0.03829 0.03408 -0.1022 0.9205 0.0066 -14.750 -0.8924 0.03453 0.03009 -0.1040 0.8726 0.0066 -14.500 -0.8924 0.03115 0.02635 -0.1066 0.8180 0.0067 -14.250 -0.8866 0.02804 0.02304 -0.1098 0.7989 0.0068 -14.000 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0.6834 0.0125 -8.750 -0.4224 0.01301 0.00642 -0.1085 0.6789 0.0131 -8.500 -0.3952 0.01273 0.00609 -0.1086 0.6749 0.0140 -8.250 -0.3678 0.01241 0.00576 -0.1087 0.6705 0.0152 -8.000 -0.3401 0.01215 0.00546 -0.1088 0.6655 0.0165 -7.750 -0.3126 0.01190 0.00516 -0.1089 0.6603 0.0186 -7.500 -0.2848 0.01161 0.00487 -0.1091 0.6552 0.0220 -7.250 -0.2575 0.01128 0.00456 -0.1092 0.6487 0.0306 -7.000 -0.2304 0.01094 0.00425 -0.1093 0.6424 0.0444 -6.750 -0.2028 0.01062 0.00399 -0.1095 0.6350 0.0586 -6.500 -0.1749 0.01041 0.00377 -0.1097 0.6275 0.0687 -6.250 -0.1464 0.01026 0.00360 -0.1099 0.6191 0.0757 -6.000 -0.1184 0.01008 0.00341 -0.1101 0.6083 0.0850 -5.500 -0.0636 0.00968 0.00304 -0.1103 0.5794 0.1251 -5.250 -0.0357 0.00953 0.00291 -0.1105 0.5681 0.1451 -5.000 -0.0074 0.00942 0.00280 -0.1108 0.5600 0.1608 -4.750 0.0211 0.00935 0.00272 -0.1110 0.5518 0.1727 -4.500 0.0496 0.00925 0.00263 -0.1112 0.5452 0.1863 -4.250 0.0783 0.00919 0.00255 -0.1115 0.5387 0.1956 -3.750 0.1359 0.00908 0.00242 -0.1120 0.5290 0.2149 -3.500 0.1648 0.00900 0.00235 -0.1123 0.5254 0.2266 -3.250 0.1936 0.00893 0.00229 -0.1126 0.5219 0.2411 -2.750 0.2504 0.00867 0.00222 -0.1132 0.5150 0.3077 -2.500 0.2796 0.00864 0.00223 -0.1135 0.5122 0.3269 -2.250 0.3089 0.00864 0.00223 -0.1139 0.5097 0.3362 -2.000 0.3381 0.00866 0.00224 -0.1142 0.5072 0.3453 -1.750 0.3672 0.00867 0.00225 -0.1145 0.5047 0.3530 -1.500 0.3961 0.00871 0.00227 -0.1148 0.5023 0.3594 -1.250 0.4251 0.00877 0.00229 -0.1151 0.4996 0.3631 -1.000 0.4544 0.00877 0.00230 -0.1154 0.4975 0.3667 -0.750 0.4836 0.00878 0.00232 -0.1158 0.4949 0.3702 -0.500 0.5127 0.00881 0.00234 -0.1161 0.4925 0.3735 -0.250 0.5416 0.00886 0.00237 -0.1164 0.4899 0.3769 0.000 0.5703 0.00891 0.00240 -0.1167 0.4871 0.3802 0.250 0.5987 0.00896 0.00245 -0.1169 0.4842 0.3843 0.500 0.6276 0.00899 0.00249 -0.1172 0.4819 0.3877 0.750 0.6566 0.00902 0.00252 -0.1175 0.4799 0.3911 1.000 0.6855 0.00906 0.00257 -0.1178 0.4775 0.3947 1.250 0.7142 0.00910 0.00261 -0.1181 0.4747 0.3980 1.500 0.7424 0.00915 0.00267 -0.1183 0.4710 0.4014 1.750 0.7702 0.00922 0.00274 -0.1185 0.4674 0.4056 2.000 0.7988 0.00926 0.00279 -0.1188 0.4644 0.4094 2.250 0.8272 0.00932 0.00285 -0.1190 0.4594 0.4117 2.500 0.8545 0.00941 0.00292 -0.1191 0.4528 0.4143 2.750 0.8823 0.00947 0.00299 -0.1192 0.4472 0.4178 3.000 0.9098 0.00955 0.00307 -0.1193 0.4396 0.4211 3.250 0.9364 0.00967 0.00317 -0.1193 0.4288 0.4243 3.500 0.9561 0.01014 0.00341 -0.1180 0.3800 0.4273 4.000 0.9917 0.01124 0.00416 -0.1149 0.3156 0.4344 4.250 1.0156 0.01145 0.00437 -0.1144 0.3083 0.4392 4.500 1.0395 0.01165 0.00456 -0.1138 0.3030 0.4444 4.750 1.0629 0.01185 0.00477 -0.1133 0.2983 0.4506 5.000 1.0872 0.01200 0.00496 -0.1128 0.2954 0.4589 5.250 1.1107 0.01213 0.00514 -0.1122 0.2930 0.4689 5.500 1.1321 0.01227 0.00533 -0.1112 0.2905 0.4836 5.750 1.1532 0.01241 0.00555 -0.1102 0.2879 0.5082 6.000 1.1749 0.01258 0.00583 -0.1094 0.2848 0.5466 6.250 1.1960 0.01281 0.00616 -0.1085 0.2796 0.5935 6.500 1.2188 0.01296 0.00646 -0.1080 0.2739 0.6456 6.750 1.2393 0.01319 0.00683 -0.1071 0.2674 0.7072 7.000 1.2601 0.01334 0.00720 -0.1062 0.2623 0.7896 7.250 1.2754 0.01324 0.00750 -0.1039 0.2583 1.0000 7.500 1.2947 0.01364 0.00787 -0.1028 0.2519 1.0000 7.750 1.3134 0.01407 0.00827 -0.1016 0.2432 1.0000 8.000 1.3299 0.01461 0.00876 -0.1002 0.2326 1.0000 8.250 1.3439 0.01529 0.00936 -0.0985 0.2159 1.0000 8.500 1.3444 0.01668 0.01054 -0.0949 0.1805 1.0000 8.750 1.3460 0.01810 0.01183 -0.0918 0.1573 1.0000 9.000 1.3542 0.01926 0.01293 -0.0897 0.1446 1.0000 9.250 1.3632 0.02043 0.01406 -0.0879 0.1342 1.0000 9.500 1.3699 0.02181 0.01539 -0.0859 0.1204 1.0000 9.750 1.3632 0.02424 0.01763 -0.0829 0.0896 1.0000 10.000 1.3599 0.02655 0.01984 -0.0805 0.0692 1.0000 10.250 1.3440 0.02995 0.02308 -0.0772 0.0348 1.0000 10.500 1.3398 0.03254 0.02563 -0.0751 0.0146 1.0000 10.750 1.3493 0.03407 0.02719 -0.0742 0.0126 1.0000 11.000 1.3596 0.03555 0.02871 -0.0734 0.0116 1.0000 11.250 1.3689 0.03712 0.03032 -0.0725 0.0108 1.0000 11.500 1.3769 0.03884 0.03208 -0.0716 0.0100 1.0000 11.750 1.3865 0.04043 0.03371 -0.0709 0.0097 1.0000 12.000 1.3951 0.04214 0.03547 -0.0702 0.0092 1.0000 12.250 1.4030 0.04395 0.03732 -0.0695 0.0087 1.0000 12.500 1.4102 0.04583 0.03924 -0.0688 0.0083 1.0000 12.750 1.4159 0.04790 0.04135 -0.0681 0.0079 1.0000 13.000 1.4219 0.04996 0.04347 -0.0674 0.0076 1.0000 13.250 1.4287 0.05200 0.04555 -0.0669 0.0074 1.0000 13.500 1.4348 0.05413 0.04774 -0.0664 0.0071 1.0000 13.750 1.4408 0.05629 0.04994 -0.0659 0.0069 1.0000 14.000 1.4455 0.05860 0.05231 -0.0655 0.0067 1.0000 14.250 1.4500 0.06096 0.05472 -0.0651 0.0064 1.0000 14.500 1.4542 0.06340 0.05721 -0.0647 0.0062 1.0000 14.750 1.4569 0.06604 0.05990 -0.0644 0.0060 1.0000 15.000 1.4588 0.06878 0.06271 -0.0641 0.0058 1.0000 15.250 1.4607 0.07154 0.06552 -0.0639 0.0056 1.0000 15.500 1.4632 0.07425 0.06829 -0.0637 0.0055 1.0000 15.750 1.4661 0.07693 0.07103 -0.0636 0.0054 1.0000 16.000 1.4670 0.07990 0.07406 -0.0635 0.0052 1.0000 16.250 1.4687 0.08275 0.07698 -0.0635 0.0051 1.0000 16.500 1.4683 0.08591 0.08021 -0.0635 0.0050 1.0000 16.750 1.4687 0.08895 0.08331 -0.0636 0.0049 1.0000 17.000 1.4677 0.09222 0.08665 -0.0638 0.0048 1.0000 17.250 1.4666 0.09552 0.09002 -0.0640 0.0047 1.0000 17.500 1.4648 0.09896 0.09353 -0.0643 0.0046 1.0000 17.750 1.4621 0.10255 0.09719 -0.0647 0.0045 1.0000 18.000 1.4593 0.10616 0.10086 -0.0652 0.0044 1.0000 18.250 1.4541 0.11015 0.10493 -0.0658 0.0043 1.0000 18.500 1.4486 0.11423 0.10909 -0.0665 0.0042 1.0000