XFOIL Version 6.96 Calculated polar for: GOE 63 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.2035 0.09570 0.09298 -0.0313 0.7062 0.0145 -8.000 -0.1942 0.09296 0.09021 -0.0329 0.6994 0.0147 -7.750 -0.1869 0.08934 0.08657 -0.0355 0.6926 0.0157 -7.250 -0.1662 0.08388 0.08107 -0.0397 0.6800 0.0160 -7.000 -0.1512 0.08150 0.07867 -0.0421 0.6735 0.0162 -6.750 -0.1349 0.07906 0.07620 -0.0448 0.6677 0.0164 -6.500 -0.1172 0.07646 0.07359 -0.0479 0.6624 0.0167 -6.250 -0.0968 0.07361 0.07070 -0.0519 0.6562 0.0182 -6.000 -0.0755 0.07032 0.06737 -0.0564 0.6501 0.0183 -5.750 -0.0512 0.06678 0.06378 -0.0617 0.6442 0.0184 -5.500 -0.0257 0.06331 0.06026 -0.0668 0.6380 0.0184 -5.250 0.0019 0.05983 0.05671 -0.0721 0.6330 0.0184 -5.000 0.0321 0.05627 0.05309 -0.0777 0.6284 0.0185 -4.750 0.0630 0.05284 0.04959 -0.0828 0.6234 0.0185 -4.500 0.0907 0.04974 0.04642 -0.0865 0.6184 0.0186 -4.250 0.1144 0.04795 0.04461 -0.0880 0.6138 0.0188 -4.000 0.1414 0.04613 0.04275 -0.0903 0.6088 0.0190 -3.750 0.1704 0.04420 0.04077 -0.0930 0.6038 0.0196 -3.250 0.2445 0.03835 0.03469 -0.1017 0.5942 0.0213 -3.000 0.2775 0.03578 0.03203 -0.1047 0.5882 0.0213 -2.500 0.3398 0.03161 0.02768 -0.1092 0.5780 0.0204 -2.250 0.3744 0.02930 0.02526 -0.1117 0.5737 0.0202 -2.000 0.4090 0.02715 0.02297 -0.1139 0.5685 0.0204 -1.750 0.4436 0.02499 0.02066 -0.1159 0.5635 0.0203 -1.500 0.4788 0.02278 0.01828 -0.1178 0.5584 0.0203 -1.250 0.5143 0.02056 0.01586 -0.1194 0.5529 0.0207 -1.000 0.5494 0.01836 0.01341 -0.1208 0.5476 0.0209 -0.750 0.5841 0.01621 0.01102 -0.1220 0.5419 0.0211 -0.500 0.6238 0.01144 0.00549 -0.1241 0.5349 0.0218 -0.250 0.6531 0.01111 0.00506 -0.1243 0.5263 0.0221 0.000 0.6824 0.01082 0.00467 -0.1245 0.5163 0.0223 0.250 0.7116 0.01052 0.00427 -0.1247 0.5056 0.0227 0.500 0.7406 0.01027 0.00390 -0.1248 0.4907 0.0230 0.750 0.7692 0.01010 0.00359 -0.1249 0.4704 0.0233 1.000 0.7974 0.01005 0.00336 -0.1250 0.4426 0.0237 1.250 0.8250 0.01014 0.00324 -0.1250 0.4045 0.0240 1.500 0.8526 0.01028 0.00320 -0.1249 0.3737 0.0245 1.750 0.8804 0.01040 0.00320 -0.1249 0.3531 0.0249 2.000 0.9087 0.01038 0.00311 -0.1250 0.3381 0.0253 2.250 0.9369 0.01041 0.00309 -0.1251 0.3268 0.0258 2.500 0.9649 0.01050 0.00313 -0.1251 0.3159 0.0264 2.750 0.9931 0.01056 0.00316 -0.1252 0.3070 0.0270 3.000 1.0211 0.01065 0.00322 -0.1252 0.2986 0.0277 3.250 1.0492 0.01071 0.00327 -0.1252 0.2917 0.0284 3.500 1.0769 0.01084 0.00335 -0.1252 0.2837 0.0289 3.750 1.1051 0.01089 0.00341 -0.1253 0.2784 0.0304 4.000 1.1328 0.01101 0.00352 -0.1253 0.2717 0.0319 4.250 1.1603 0.01115 0.00363 -0.1252 0.2647 0.0333 4.500 1.1880 0.01126 0.00374 -0.1252 0.2580 0.0361 4.750 1.2152 0.01142 0.00389 -0.1251 0.2512 0.0438 5.000 1.2428 0.01151 0.00406 -0.1251 0.2452 0.0942 5.500 1.2920 0.01063 0.00462 -0.1243 0.2294 1.0000 5.750 1.3185 0.01089 0.00481 -0.1242 0.2208 1.0000 6.000 1.3451 0.01111 0.00499 -0.1240 0.2135 1.0000 6.500 1.3972 0.01165 0.00544 -0.1236 0.1964 1.0000 6.750 1.4227 0.01196 0.00569 -0.1233 0.1876 1.0000 7.000 1.4481 0.01227 0.00596 -0.1230 0.1786 1.0000 7.250 1.4730 0.01261 0.00625 -0.1226 0.1693 1.0000 7.500 1.4970 0.01302 0.00658 -0.1221 0.1585 1.0000 7.750 1.5213 0.01338 0.00690 -0.1217 0.1502 1.0000 8.000 1.5456 0.01373 0.00722 -0.1212 0.1438 1.0000 8.250 1.5695 0.01409 0.00755 -0.1207 0.1370 1.0000 8.500 1.5930 0.01447 0.00791 -0.1202 0.1312 1.0000 8.750 1.6164 0.01484 0.00826 -0.1196 0.1254 1.0000 9.000 1.6385 0.01530 0.00867 -0.1189 0.1182 1.0000 9.250 1.6612 0.01568 0.00905 -0.1182 0.1131 1.0000 9.500 1.6825 0.01615 0.00949 -0.1173 0.1073 1.0000 9.750 1.7044 0.01654 0.00989 -0.1165 0.1036 1.0000 10.000 1.7251 0.01701 0.01034 -0.1156 0.0986 1.0000 10.250 1.7444 0.01753 0.01085 -0.1144 0.0932 1.0000 10.500 1.7639 0.01801 0.01134 -0.1133 0.0888 1.0000 10.750 1.7802 0.01864 0.01193 -0.1117 0.0829 1.0000 11.000 1.7962 0.01924 0.01253 -0.1100 0.0768 1.0000 11.250 1.8080 0.01999 0.01325 -0.1077 0.0696 1.0000 11.500 1.8131 0.02100 0.01422 -0.1043 0.0594 1.0000 11.750 1.8018 0.02321 0.01625 -0.0992 0.0355 1.0000 12.000 1.7924 0.02564 0.01861 -0.0951 0.0185 1.0000 12.250 1.7987 0.02709 0.02011 -0.0932 0.0159 1.0000 12.500 1.8058 0.02858 0.02165 -0.0915 0.0145 1.0000 12.750 1.8146 0.03001 0.02314 -0.0902 0.0138 1.0000 13.000 1.8223 0.03161 0.02480 -0.0890 0.0131 1.0000 13.250 1.8287 0.03336 0.02662 -0.0878 0.0125 1.0000 13.500 1.8338 0.03531 0.02863 -0.0867 0.0120 1.0000 13.750 1.8389 0.03729 0.03068 -0.0857 0.0115 1.0000 14.000 1.8445 0.03927 0.03274 -0.0848 0.0113 1.0000 14.250 1.8485 0.04141 0.03496 -0.0840 0.0110 1.0000 14.500 1.8514 0.04374 0.03737 -0.0832 0.0107 1.0000 14.750 1.8531 0.04623 0.03993 -0.0825 0.0103 1.0000 15.000 1.8532 0.04892 0.04270 -0.0818 0.0100 1.0000 15.250 1.8518 0.05183 0.04569 -0.0812 0.0097 1.0000 15.500 1.8492 0.05497 0.04891 -0.0807 0.0095 1.0000 15.750 1.8448 0.05839 0.05243 -0.0804 0.0092 1.0000 16.000 1.8415 0.06177 0.05590 -0.0802 0.0090 1.0000 16.250 1.8382 0.06522 0.05945 -0.0801 0.0089 1.0000 16.500 1.8339 0.06890 0.06322 -0.0802 0.0088 1.0000 16.750 1.8284 0.07280 0.06722 -0.0804 0.0087 1.0000 17.000 1.8216 0.07695 0.07147 -0.0807 0.0085 1.0000 17.250 1.8135 0.08138 0.07601 -0.0813 0.0084 1.0000 17.500 1.8045 0.08604 0.08079 -0.0820 0.0083 1.0000 17.750 1.7940 0.09099 0.08584 -0.0829 0.0082 1.0000 18.000 1.7821 0.09623 0.09119 -0.0840 0.0081 1.0000 18.250 1.7687 0.10184 0.09692 -0.0854 0.0080 1.0000 18.500 1.7545 0.10768 0.10288 -0.0871 0.0079 1.0000 18.750 1.7397 0.11366 0.10898 -0.0889 0.0078 1.0000 19.000 1.7241 0.11988 0.11532 -0.0910 0.0078 1.0000 19.250 1.7079 0.12633 0.12189 -0.0934 0.0077 1.0000