XFOIL Version 6.96 Calculated polar for: GOE 797 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.7316 0.10747 0.10509 -0.0683 1.0000 0.0298 -17.250 -0.8013 0.09197 0.08940 -0.0777 1.0000 0.0301 -17.000 -0.8542 0.08035 0.07762 -0.0851 1.0000 0.0302 -16.750 -0.9104 0.06857 0.06568 -0.0928 1.0000 0.0302 -16.500 -0.9616 0.05747 0.05440 -0.1003 1.0000 0.0302 -16.250 -1.0017 0.04723 0.04397 -0.1082 1.0000 0.0302 -16.000 -1.0314 0.03947 0.03604 -0.1144 1.0000 0.0302 -15.750 -1.0526 0.03481 0.03123 -0.1171 0.9987 0.0303 -15.500 -1.0427 0.03166 0.02797 -0.1213 0.9956 0.0306 -15.250 -1.0280 0.02950 0.02571 -0.1240 0.9934 0.0308 -15.000 -1.0135 0.02789 0.02401 -0.1251 0.9898 0.0311 -14.750 -0.9973 0.02658 0.02262 -0.1255 0.9853 0.0313 -14.500 -0.9778 0.02543 0.02139 -0.1260 0.9818 0.0316 -14.250 -0.9620 0.02448 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0.0783 -4.250 0.0454 0.00939 0.00304 -0.1148 0.6985 0.0835 -4.000 0.0741 0.00931 0.00294 -0.1149 0.6935 0.0892 -3.750 0.1034 0.00923 0.00287 -0.1152 0.6898 0.0947 -3.500 0.1327 0.00911 0.00280 -0.1155 0.6858 0.1015 -3.250 0.1620 0.00907 0.00274 -0.1157 0.6811 0.1064 -3.000 0.1908 0.00901 0.00269 -0.1159 0.6764 0.1130 -2.750 0.2202 0.00899 0.00265 -0.1162 0.6726 0.1177 -2.500 0.2496 0.00889 0.00259 -0.1165 0.6689 0.1233 -2.250 0.2789 0.00884 0.00255 -0.1167 0.6644 0.1285 -2.000 0.3080 0.00885 0.00252 -0.1169 0.6596 0.1320 -1.750 0.3370 0.00878 0.00246 -0.1172 0.6547 0.1377 -1.500 0.3664 0.00871 0.00242 -0.1175 0.6503 0.1430 -1.250 0.3958 0.00870 0.00239 -0.1177 0.6461 0.1466 -1.000 0.4247 0.00865 0.00234 -0.1179 0.6421 0.1524 -0.750 0.4536 0.00863 0.00232 -0.1182 0.6380 0.1585 -0.500 0.4832 0.00858 0.00230 -0.1185 0.6346 0.1633 -0.250 0.5124 0.00851 0.00227 -0.1188 0.6305 0.1725 0.000 0.5414 0.00848 0.00225 -0.1190 0.6262 0.1814 0.250 0.5698 0.00845 0.00225 -0.1192 0.6215 0.1987 0.500 0.5988 0.00831 0.00225 -0.1195 0.6175 0.2358 0.750 0.6274 0.00815 0.00227 -0.1198 0.6125 0.2962 1.000 0.6555 0.00798 0.00229 -0.1200 0.6073 0.3669 1.250 0.6828 0.00769 0.00234 -0.1201 0.6024 0.4931 1.500 0.7098 0.00728 0.00241 -0.1202 0.5975 0.6567 1.750 0.7350 0.00697 0.00250 -0.1196 0.5919 0.7960 2.000 0.7576 0.00685 0.00261 -0.1182 0.5861 0.8889 2.250 0.7818 0.00681 0.00268 -0.1171 0.5806 0.9467 2.500 0.8142 0.00688 0.00273 -0.1179 0.5736 0.9788 2.750 0.8513 0.00698 0.00279 -0.1200 0.5663 0.9930 3.000 0.8911 0.00708 0.00285 -0.1227 0.5569 0.9992 3.250 0.9175 0.00719 0.00291 -0.1225 0.5466 1.0000 3.500 0.9412 0.00733 0.00297 -0.1217 0.5335 1.0000 3.750 0.9651 0.00750 0.00306 -0.1209 0.5179 1.0000 4.000 0.9890 0.00769 0.00317 -0.1202 0.5003 1.0000 4.250 1.0126 0.00792 0.00330 -0.1195 0.4801 1.0000 4.500 1.0354 0.00820 0.00347 -0.1186 0.4582 1.0000 5.000 1.0782 0.00891 0.00392 -0.1163 0.4102 1.0000 5.250 1.1000 0.00924 0.00415 -0.1153 0.3920 1.0000 5.500 1.1223 0.00954 0.00437 -0.1144 0.3785 1.0000 6.000 1.1674 0.01008 0.00481 -0.1126 0.3579 1.0000 6.250 1.1888 0.01038 0.00505 -0.1115 0.3496 1.0000 6.500 1.2118 0.01059 0.00526 -0.1107 0.3434 1.0000 6.750 1.2327 0.01086 0.00550 -0.1095 0.3367 1.0000 7.000 1.2513 0.01116 0.00577 -0.1079 0.3307 1.0000 7.250 1.2730 0.01137 0.00598 -0.1069 0.3266 1.0000 7.500 1.2936 0.01163 0.00625 -0.1056 0.3221 1.0000 7.750 1.3127 0.01197 0.00656 -0.1042 0.3172 1.0000 8.000 1.3331 0.01227 0.00687 -0.1030 0.3130 1.0000 8.250 1.3552 0.01251 0.00713 -0.1022 0.3093 1.0000 8.500 1.3758 0.01282 0.00745 -0.1011 0.3051 1.0000 8.750 1.3945 0.01322 0.00783 -0.0998 0.3001 1.0000 9.000 1.4146 0.01356 0.00819 -0.0987 0.2957 1.0000 9.250 1.4362 0.01385 0.00850 -0.0979 0.2911 1.0000 9.500 1.4549 0.01428 0.00892 -0.0967 0.2854 1.0000 9.750 1.4732 0.01473 0.00937 -0.0954 0.2793 1.0000 10.000 1.4932 0.01512 0.00976 -0.0944 0.2721 1.0000 10.250 1.5092 0.01571 0.01032 -0.0929 0.2638 1.0000 10.500 1.5273 0.01621 0.01081 -0.0917 0.2539 1.0000 10.750 1.5422 0.01688 0.01145 -0.0902 0.2418 1.0000 11.000 1.5545 0.01772 0.01222 -0.0883 0.2263 1.0000 11.250 1.5614 0.01890 0.01328 -0.0858 0.2047 1.0000 11.500 1.5658 0.02027 0.01452 -0.0831 0.1846 1.0000 11.750 1.5722 0.02157 0.01576 -0.0808 0.1715 1.0000 12.250 1.5915 0.02388 0.01803 -0.0773 0.1559 1.0000 12.500 1.6012 0.02508 0.01923 -0.0756 0.1503 1.0000 12.750 1.6121 0.02623 0.02040 -0.0742 0.1454 1.0000 13.000 1.6241 0.02733 0.02151 -0.0730 0.1408 1.0000 13.250 1.6323 0.02874 0.02292 -0.0715 0.1354 1.0000 13.500 1.6434 0.02996 0.02417 -0.0703 0.1311 1.0000 13.750 1.6541 0.03124 0.02546 -0.0692 0.1267 1.0000 14.000 1.6617 0.03280 0.02703 -0.0678 0.1220 1.0000 14.250 1.6723 0.03415 0.02842 -0.0668 0.1182 1.0000 14.500 1.6808 0.03570 0.02997 -0.0657 0.1132 1.0000 14.750 1.6868 0.03748 0.03175 -0.0645 0.1083 1.0000 15.000 1.6954 0.03905 0.03336 -0.0636 0.1039 1.0000 15.250 1.6998 0.04103 0.03532 -0.0624 0.0987 1.0000 15.500 1.7066 0.04284 0.03717 -0.0615 0.0945 1.0000 15.750 1.7103 0.04494 0.03927 -0.0605 0.0895 1.0000 16.000 1.7144 0.04702 0.04138 -0.0595 0.0852 1.0000 16.250 1.7161 0.04938 0.04375 -0.0585 0.0803 1.0000 16.500 1.7184 0.05172 0.04611 -0.0576 0.0758 1.0000 16.750 1.7175 0.05444 0.04883 -0.0567 0.0709 1.0000 17.000 1.7173 0.05712 0.05154 -0.0560 0.0665 1.0000 17.250 1.7136 0.06019 0.05462 -0.0552 0.0617 1.0000 17.500 1.7110 0.06322 0.05768 -0.0545 0.0568 1.0000 17.750 1.7052 0.06669 0.06116 -0.0539 0.0517 1.0000 18.000 1.6970 0.07048 0.06497 -0.0534 0.0464 1.0000 18.250 1.6860 0.07465 0.06915 -0.0530 0.0401 1.0000 18.500 1.6727 0.07921 0.07372 -0.0528 0.0339 1.0000 18.750 1.6577 0.08410 0.07863 -0.0527 0.0284 1.0000