XFOIL Version 6.96 Calculated polar for: GOE 490 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.2972 0.08684 0.08476 -0.0311 1.0000 0.0256 -9.000 -0.2958 0.08428 0.08221 -0.0306 1.0000 0.0262 -8.750 -0.3977 0.08762 0.08546 -0.0316 1.0000 0.0246 -8.500 -0.3928 0.08637 0.08422 -0.0300 1.0000 0.0252 -8.250 -0.3929 0.08453 0.08242 -0.0289 1.0000 0.0257 -8.000 -0.3965 0.08281 0.08073 -0.0275 1.0000 0.0264 -7.000 -0.4282 0.02889 0.02562 -0.0663 0.9819 0.0221 -6.750 -0.4072 0.02430 0.02035 -0.0674 0.9762 0.0234 -6.500 -0.3797 0.02090 0.01641 -0.0689 0.9731 0.0251 -6.250 -0.3437 0.02004 0.01548 -0.0712 0.9713 0.0265 -6.000 -0.3180 0.01904 0.01435 -0.0709 0.9647 0.0278 -5.750 -0.2844 0.01787 0.01294 -0.0722 0.9614 0.0295 -5.500 -0.2468 0.01764 0.01255 -0.0741 0.9593 0.0312 -5.250 -0.2208 0.01502 0.00960 -0.0742 0.9547 0.0333 -5.000 -0.1899 0.01422 0.00872 -0.0749 0.9498 0.0348 -4.750 -0.1542 0.01356 0.00798 -0.0765 0.9470 0.0370 -4.500 -0.1158 0.01286 0.00716 -0.0785 0.9446 0.0388 -4.250 -0.0867 0.01224 0.00644 -0.0786 0.9367 0.0398 -4.000 -0.0517 0.01148 0.00557 -0.0799 0.9320 0.0413 -3.750 -0.0205 0.01062 0.00463 -0.0806 0.9253 0.0432 -3.500 0.0128 0.01009 0.00407 -0.0816 0.9182 0.0451 -3.250 0.0444 0.00971 0.00364 -0.0822 0.9092 0.0470 -3.000 0.0784 0.00939 0.00325 -0.0833 0.9011 0.0498 -2.750 0.1067 0.00916 0.00296 -0.0832 0.8896 0.0514 -2.500 0.1345 0.00881 0.00258 -0.0829 0.8777 0.0572 -2.250 0.1621 0.00855 0.00233 -0.0826 0.8654 0.0690 -2.000 0.1889 0.00832 0.00223 -0.0822 0.8529 0.1149 -1.750 0.2161 0.00827 0.00216 -0.0819 0.8400 0.1338 -1.500 0.2426 0.00823 0.00208 -0.0814 0.8261 0.1463 -1.250 0.2684 0.00815 0.00198 -0.0808 0.8117 0.1574 -1.000 0.2939 0.00809 0.00189 -0.0801 0.7971 0.1689 -0.750 0.3191 0.00803 0.00182 -0.0794 0.7815 0.1834 -0.500 0.3436 0.00796 0.00178 -0.0785 0.7635 0.2075 -0.250 0.3679 0.00794 0.00178 -0.0776 0.7434 0.2438 0.250 0.4166 0.00794 0.00176 -0.0758 0.7053 0.3082 0.500 0.4406 0.00789 0.00173 -0.0749 0.6878 0.3338 0.750 0.4633 0.00773 0.00172 -0.0737 0.6696 0.3921 1.000 0.5537 0.00669 0.00203 -0.0874 0.6380 0.9883 1.250 0.6102 0.00689 0.00204 -0.0938 0.6073 1.0000 1.500 0.6320 0.00703 0.00206 -0.0924 0.5826 1.0000 1.750 0.6533 0.00720 0.00209 -0.0909 0.5555 1.0000 2.000 0.6743 0.00740 0.00214 -0.0894 0.5277 1.0000 2.250 0.6954 0.00760 0.00220 -0.0879 0.5024 1.0000 2.500 0.7172 0.00779 0.00230 -0.0866 0.4821 1.0000 2.750 0.7392 0.00798 0.00239 -0.0853 0.4650 1.0000 3.000 0.7614 0.00817 0.00251 -0.0841 0.4507 1.0000 3.250 0.7836 0.00835 0.00263 -0.0829 0.4376 1.0000 3.500 0.8059 0.00854 0.00277 -0.0817 0.4254 1.0000 3.750 0.8281 0.00874 0.00290 -0.0805 0.4133 1.0000 4.000 0.8508 0.00890 0.00304 -0.0794 0.4013 1.0000 4.250 0.8732 0.00908 0.00319 -0.0782 0.3881 1.0000 4.500 0.8946 0.00931 0.00334 -0.0769 0.3690 1.0000 4.750 0.9159 0.00953 0.00348 -0.0756 0.3440 1.0000 5.000 0.9371 0.00978 0.00365 -0.0742 0.3235 1.0000 5.250 0.9579 0.01006 0.00385 -0.0729 0.2983 1.0000 5.500 0.9775 0.01042 0.00407 -0.0713 0.2706 1.0000 5.750 0.9970 0.01080 0.00433 -0.0697 0.2466 1.0000 6.250 1.0360 0.01159 0.00492 -0.0666 0.2039 1.0000 6.500 1.0547 0.01204 0.00525 -0.0649 0.1798 1.0000 6.750 1.0728 0.01255 0.00560 -0.0632 0.1508 1.0000 7.000 1.0901 0.01311 0.00599 -0.0613 0.1247 1.0000 7.250 1.1056 0.01380 0.00648 -0.0592 0.0910 1.0000 7.500 1.1109 0.01523 0.00750 -0.0553 0.0255 1.0000 7.750 1.1278 0.01580 0.00807 -0.0533 0.0197 1.0000 8.000 1.1455 0.01631 0.00866 -0.0515 0.0182 1.0000 8.250 1.1615 0.01693 0.00936 -0.0494 0.0168 1.0000 8.500 1.1760 0.01765 0.01017 -0.0470 0.0158 1.0000 8.750 1.1885 0.01845 0.01109 -0.0443 0.0152 1.0000 9.000 1.2013 0.01911 0.01184 -0.0417 0.0149 1.0000 9.250 1.2107 0.01985 0.01267 -0.0385 0.0144 1.0000 9.500 1.2197 0.02062 0.01352 -0.0354 0.0141 1.0000 9.750 1.2272 0.02151 0.01449 -0.0322 0.0136 1.0000 10.000 1.2334 0.02250 0.01556 -0.0290 0.0130 1.0000 10.250 1.2388 0.02358 0.01671 -0.0259 0.0126 1.0000 10.500 1.2420 0.02485 0.01805 -0.0227 0.0123 1.0000 10.750 1.2446 0.02622 0.01952 -0.0198 0.0121 1.0000 11.000 1.2444 0.02790 0.02128 -0.0168 0.0119 1.0000 11.250 1.2437 0.02977 0.02322 -0.0142 0.0117 1.0000 11.500 1.2430 0.03181 0.02534 -0.0117 0.0115 1.0000 11.750 1.2442 0.03392 0.02751 -0.0097 0.0114 1.0000 12.000 1.2479 0.03605 0.02971 -0.0078 0.0113 1.0000 12.250 1.2549 0.03831 0.03203 -0.0060 0.0112 1.0000 12.500 1.2582 0.03996 0.03384 -0.0049 0.0110 1.0000 12.750 1.2630 0.04192 0.03592 -0.0037 0.0108 1.0000 13.000 1.2715 0.04408 0.03816 -0.0023 0.0110 1.0000 13.250 1.2754 0.04633 0.04055 -0.0013 0.0109 1.0000 13.500 1.2783 0.04878 0.04313 -0.0003 0.0108 1.0000 13.750 1.2754 0.05129 0.04581 0.0000 0.0106 1.0000 14.000 1.2797 0.05433 0.04898 0.0012 0.0108 1.0000 14.250 1.2743 0.05735 0.05216 0.0012 0.0106 1.0000 14.500 1.2694 0.06067 0.05565 0.0010 0.0104 1.0000 14.750 1.2647 0.06419 0.05932 0.0007 0.0104 1.0000 15.000 1.2577 0.06812 0.06341 0.0000 0.0104 1.0000 15.250 1.2496 0.07245 0.06790 -0.0007 0.0105 1.0000 15.500 1.2393 0.07719 0.07280 -0.0022 0.0105 1.0000 15.750 1.2273 0.08264 0.07842 -0.0031 0.0108 1.0000 16.250 1.0749 0.09438 0.09070 -0.0059 0.0115 1.0000 16.500 1.0504 0.09981 0.09632 -0.0098 0.0115 1.0000 16.750 1.0294 0.10568 0.10238 -0.0142 0.0117 1.0000 17.250 0.9480 0.12656 0.12396 -0.0300 0.0132 1.0000 17.500 0.9205 0.13523 0.13282 -0.0362 0.0138 1.0000