XFOIL Version 6.96 Calculated polar for: GOE 497 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.7577 0.08020 0.07764 -0.0773 1.0000 0.0170 -15.500 -0.7968 0.07161 0.06896 -0.0821 1.0000 0.0169 -15.250 -0.8441 0.06292 0.06016 -0.0867 1.0000 0.0169 -15.000 -0.8899 0.05149 0.04855 -0.0978 0.9977 0.0166 -14.750 -0.9342 0.03828 0.03511 -0.1140 0.9843 0.0164 -14.500 -0.9313 0.02540 0.02185 -0.1374 0.9735 0.0167 -14.250 -0.9024 0.02311 0.01943 -0.1425 0.9703 0.0175 -14.000 -0.8758 0.02165 0.01785 -0.1452 0.9645 0.0182 -13.750 -0.8449 0.02049 0.01658 -0.1479 0.9599 0.0188 -13.500 -0.8180 0.01939 0.01540 -0.1496 0.9523 0.0196 -13.250 -0.7892 0.01853 0.01446 -0.1512 0.9442 0.0205 -13.000 -0.7645 0.01784 0.01369 -0.1517 0.9345 0.0212 -12.750 -0.7388 0.01724 0.01299 -0.1521 0.9267 0.0219 -12.500 -0.7145 0.01671 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0.3402 0.00772 0.00158 -0.1485 0.6478 0.1169 -2.500 0.3681 0.00768 0.00153 -0.1484 0.6393 0.1244 -2.250 0.3957 0.00766 0.00150 -0.1482 0.6316 0.1335 -2.000 0.4237 0.00760 0.00146 -0.1482 0.6245 0.1467 -1.500 0.4789 0.00753 0.00143 -0.1479 0.6075 0.1797 -1.250 0.5061 0.00753 0.00143 -0.1476 0.5972 0.1975 -1.000 0.5340 0.00751 0.00143 -0.1475 0.5890 0.2132 -0.750 0.5614 0.00752 0.00145 -0.1473 0.5812 0.2256 -0.500 0.5892 0.00753 0.00146 -0.1472 0.5723 0.2360 -0.250 0.6165 0.00756 0.00149 -0.1470 0.5627 0.2482 0.000 0.6435 0.00761 0.00152 -0.1467 0.5503 0.2594 0.250 0.6700 0.00770 0.00156 -0.1463 0.5335 0.2685 0.500 0.6957 0.00783 0.00163 -0.1458 0.5095 0.2789 0.750 0.7208 0.00801 0.00172 -0.1452 0.4853 0.2881 1.000 0.7464 0.00817 0.00181 -0.1447 0.4665 0.2982 1.250 0.7722 0.00831 0.00191 -0.1442 0.4527 0.3090 1.500 0.7983 0.00842 0.00201 -0.1438 0.4405 0.3238 1.750 0.8245 0.00852 0.00211 -0.1434 0.4307 0.3416 2.000 0.8507 0.00862 0.00222 -0.1431 0.4226 0.3561 2.250 0.8773 0.00870 0.00232 -0.1427 0.4165 0.3719 2.500 0.9037 0.00879 0.00243 -0.1424 0.4093 0.3890 2.750 0.9296 0.00891 0.00255 -0.1420 0.4029 0.4038 3.000 0.9565 0.00897 0.00265 -0.1417 0.3984 0.4171 3.250 0.9830 0.00905 0.00276 -0.1414 0.3935 0.4306 3.500 1.0090 0.00915 0.00289 -0.1410 0.3885 0.4460 3.750 1.0351 0.00924 0.00301 -0.1406 0.3840 0.4606 4.000 1.0611 0.00935 0.00314 -0.1402 0.3765 0.4746 4.250 1.0857 0.00951 0.00330 -0.1395 0.3633 0.4910 4.500 1.1094 0.00973 0.00347 -0.1387 0.3441 0.5087 4.750 1.1318 0.01000 0.00368 -0.1378 0.3210 0.5281 5.000 1.1531 0.01032 0.00393 -0.1366 0.2936 0.5550 5.250 1.1733 0.01066 0.00423 -0.1352 0.2678 0.5942 5.500 1.1928 0.01075 0.00459 -0.1338 0.2500 0.7460 6.000 1.2348 0.01104 0.00515 -0.1312 0.2236 1.0000 6.250 1.2571 0.01130 0.00539 -0.1302 0.2170 1.0000 6.500 1.2789 0.01157 0.00563 -0.1291 0.2112 1.0000 6.750 1.3004 0.01178 0.00585 -0.1279 0.2064 1.0000 7.000 1.3197 0.01208 0.00611 -0.1263 0.1995 1.0000 7.250 1.3395 0.01235 0.00638 -0.1248 0.1937 1.0000 7.500 1.3584 0.01266 0.00666 -0.1232 0.1847 1.0000 7.750 1.3765 0.01301 0.00697 -0.1215 0.1747 1.0000 8.000 1.3895 0.01361 0.00742 -0.1190 0.1506 1.0000 8.250 1.3963 0.01451 0.00812 -0.1156 0.1180 1.0000 8.500 1.4080 0.01519 0.00872 -0.1130 0.1028 1.0000 8.750 1.4220 0.01578 0.00926 -0.1109 0.0925 1.0000 9.000 1.4364 0.01635 0.00980 -0.1089 0.0854 1.0000 9.250 1.4515 0.01691 0.01034 -0.1070 0.0793 1.0000 9.500 1.4661 0.01750 0.01092 -0.1051 0.0743 1.0000 9.750 1.4818 0.01804 0.01147 -0.1034 0.0706 1.0000 10.000 1.4960 0.01868 0.01210 -0.1016 0.0667 1.0000 10.250 1.5104 0.01933 0.01275 -0.0999 0.0630 1.0000 10.500 1.5246 0.02000 0.01343 -0.0982 0.0595 1.0000 10.750 1.5370 0.02079 0.01422 -0.0963 0.0558 1.0000 11.000 1.5513 0.02149 0.01494 -0.0947 0.0537 1.0000 11.250 1.5650 0.02224 0.01572 -0.0931 0.0515 1.0000 11.500 1.5772 0.02312 0.01660 -0.0915 0.0488 1.0000 11.750 1.5887 0.02406 0.01756 -0.0898 0.0457 1.0000 12.000 1.6006 0.02500 0.01852 -0.0882 0.0428 1.0000 12.250 1.6096 0.02617 0.01968 -0.0864 0.0388 1.0000 12.500 1.6190 0.02735 0.02087 -0.0848 0.0345 1.0000 12.750 1.6249 0.02883 0.02233 -0.0829 0.0285 1.0000 13.000 1.6265 0.03070 0.02417 -0.0809 0.0208 1.0000 13.250 1.6300 0.03249 0.02597 -0.0791 0.0172 1.0000 13.500 1.6351 0.03421 0.02773 -0.0776 0.0153 1.0000 13.750 1.6412 0.03592 0.02948 -0.0763 0.0142 1.0000 14.000 1.6463 0.03776 0.03137 -0.0750 0.0133 1.0000 14.250 1.6528 0.03953 0.03319 -0.0740 0.0125 1.0000 14.500 1.6580 0.04148 0.03521 -0.0730 0.0119 1.0000 14.750 1.6619 0.04363 0.03742 -0.0720 0.0113 1.0000 15.000 1.6654 0.04590 0.03974 -0.0712 0.0108 1.0000 15.250 1.6698 0.04812 0.04203 -0.0705 0.0104 1.0000 15.500 1.6741 0.05041 0.04440 -0.0700 0.0102 1.0000 15.750 1.6773 0.05290 0.04696 -0.0695 0.0098 1.0000 16.000 1.6798 0.05554 0.04967 -0.0692 0.0095 1.0000 16.250 1.6811 0.05837 0.05257 -0.0689 0.0093 1.0000 16.500 1.6813 0.06141 0.05569 -0.0688 0.0090 1.0000 16.750 1.6808 0.06464 0.05900 -0.0689 0.0087 1.0000 17.000 1.6787 0.06817 0.06260 -0.0691 0.0084 1.0000 17.250 1.6782 0.07153 0.06605 -0.0694 0.0082 1.0000 17.500 1.6775 0.07501 0.06962 -0.0699 0.0081 1.0000 17.750 1.6759 0.07870 0.07340 -0.0705 0.0080 1.0000 18.000 1.6736 0.08259 0.07737 -0.0713 0.0077 1.0000 18.250 1.6705 0.08666 0.08153 -0.0722 0.0076 1.0000 18.500 1.6666 0.09092 0.08588 -0.0734 0.0074 1.0000 18.750 1.6620 0.09538 0.09044 -0.0747 0.0072 1.0000 19.000 1.6567 0.10000 0.09516 -0.0762 0.0071 1.0000 19.250 1.6511 0.10474 0.09999 -0.0778 0.0070 1.0000