XFOIL Version 6.96 Calculated polar for: GOE 704 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -1.0266 0.10110 0.09840 -0.0084 1.0000 0.0064 -16.500 -1.2800 0.04926 0.04577 -0.0433 1.0000 0.0055 -16.250 -1.3124 0.04126 0.03750 -0.0480 1.0000 0.0054 -16.000 -1.3242 0.03774 0.03383 -0.0476 1.0000 0.0055 -15.750 -1.3298 0.03523 0.03118 -0.0462 1.0000 0.0055 -15.500 -1.3312 0.03326 0.02909 -0.0443 1.0000 0.0055 -15.250 -1.3348 0.03125 0.02695 -0.0417 1.0000 0.0057 -15.000 -1.3344 0.02962 0.02521 -0.0390 1.0000 0.0058 -14.750 -1.3308 0.02828 0.02377 -0.0363 1.0000 0.0059 -14.500 -1.3249 0.02714 0.02254 -0.0336 1.0000 0.0060 -14.250 -1.3155 0.02613 0.02144 -0.0312 1.0000 0.0062 -14.000 -1.3024 0.02517 0.02041 -0.0294 1.0000 0.0064 -13.750 -1.2875 0.02427 0.01943 -0.0279 1.0000 0.0065 -13.500 -1.2711 0.02344 0.01852 -0.0264 1.0000 0.0067 -13.250 -1.2537 0.02264 0.01765 -0.0251 1.0000 0.0068 -13.000 -1.2352 0.02189 0.01681 -0.0239 1.0000 0.0070 -12.750 -1.2158 0.02119 0.01604 -0.0228 1.0000 0.0072 -12.500 -1.1957 0.02052 0.01530 -0.0218 1.0000 0.0074 -12.250 -1.1747 0.01990 0.01462 -0.0209 1.0000 0.0075 -12.000 -1.1544 0.01918 0.01382 -0.0199 1.0000 0.0078 -11.750 -1.1324 0.01849 0.01308 -0.0192 0.9948 0.0081 -11.500 -1.1052 0.01786 0.01238 -0.0195 0.9733 0.0085 -11.250 -1.0814 0.01733 0.01178 -0.0189 0.9505 0.0089 -11.000 -1.0607 0.01690 0.01125 -0.0176 0.9272 0.0092 -10.750 -1.0392 0.01650 0.01074 -0.0164 0.9052 0.0096 -10.500 -1.0165 0.01613 0.01026 -0.0155 0.8856 0.0099 -10.250 -0.9937 0.01567 0.00970 -0.0146 0.8681 0.0106 -10.000 -0.9702 0.01524 0.00917 -0.0138 0.8517 0.0113 -9.750 -0.9459 0.01486 0.00870 -0.0132 0.8365 0.0120 -9.500 -0.9210 0.01451 0.00826 -0.0127 0.8231 0.0127 -9.250 -0.8958 0.01415 0.00783 -0.0123 0.8118 0.0137 -9.000 -0.8706 0.01377 0.00739 -0.0118 0.8013 0.0151 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1.250 0.2614 0.00818 0.00159 -0.0101 0.4271 0.3712 1.500 0.2871 0.00818 0.00165 -0.0098 0.3957 0.4307 1.750 0.3117 0.00806 0.00170 -0.0094 0.3681 0.5218 2.000 0.3234 0.00700 0.00173 -0.0061 0.3524 0.8583 2.250 0.3498 0.00714 0.00186 -0.0057 0.3341 0.8858 2.750 0.4033 0.00748 0.00211 -0.0052 0.3012 0.9154 3.000 0.4300 0.00763 0.00224 -0.0049 0.2884 0.9258 3.250 0.4571 0.00779 0.00236 -0.0047 0.2765 0.9325 3.500 0.4834 0.00796 0.00249 -0.0044 0.2647 0.9400 3.750 0.5100 0.00813 0.00260 -0.0042 0.2538 0.9451 4.000 0.5369 0.00829 0.00274 -0.0039 0.2435 0.9500 4.250 0.5629 0.00847 0.00288 -0.0035 0.2341 0.9556 4.500 0.5888 0.00865 0.00302 -0.0032 0.2243 0.9596 4.750 0.6167 0.00881 0.00315 -0.0033 0.2156 0.9620 5.000 0.6440 0.00899 0.00330 -0.0032 0.2075 0.9650 5.250 0.6711 0.00917 0.00346 -0.0031 0.2000 0.9683 5.500 0.6973 0.00934 0.00360 -0.0029 0.1935 0.9710 5.750 0.7245 0.00949 0.00374 -0.0030 0.1878 0.9726 6.250 0.7813 0.00985 0.00407 -0.0036 0.1754 0.9746 6.500 0.8093 0.01006 0.00425 -0.0039 0.1687 0.9757 6.750 0.8372 0.01027 0.00445 -0.0041 0.1608 0.9769 7.000 0.8645 0.01053 0.00466 -0.0043 0.1522 0.9782 7.250 0.8919 0.01075 0.00487 -0.0045 0.1440 0.9797 7.500 0.9175 0.01109 0.00513 -0.0044 0.1286 0.9814 7.750 0.9380 0.01178 0.00559 -0.0036 0.0924 0.9839 8.000 0.9656 0.01217 0.00594 -0.0040 0.0838 0.9848 8.250 0.9934 0.01250 0.00626 -0.0045 0.0797 0.9858 8.500 1.0211 0.01284 0.00660 -0.0049 0.0748 0.9868 8.750 1.0491 0.01311 0.00689 -0.0053 0.0718 0.9878 9.000 1.0759 0.01348 0.00726 -0.0056 0.0663 0.9889 9.250 1.1022 0.01388 0.00764 -0.0058 0.0594 0.9901 9.500 1.1179 0.01518 0.00865 -0.0048 0.0216 0.9925 9.750 1.1405 0.01579 0.00924 -0.0044 0.0160 0.9941 10.000 1.1660 0.01630 0.00977 -0.0047 0.0138 0.9949 10.250 1.1909 0.01683 0.01031 -0.0049 0.0124 0.9960 10.500 1.2147 0.01740 0.01091 -0.0049 0.0113 0.9973 10.750 1.2391 0.01791 0.01146 -0.0051 0.0107 0.9988 11.000 1.2578 0.01844 0.01203 -0.0041 0.0101 1.0000 11.250 1.2547 0.01882 0.01244 0.0013 0.0098 1.0000 11.500 1.2606 0.01938 0.01303 0.0046 0.0093 1.0000 11.750 1.2704 0.02009 0.01377 0.0069 0.0088 1.0000 12.000 1.2820 0.02086 0.01459 0.0086 0.0084 1.0000 12.250 1.2952 0.02163 0.01540 0.0100 0.0081 1.0000 12.500 1.3080 0.02248 0.01631 0.0112 0.0079 1.0000 12.750 1.3204 0.02342 0.01731 0.0124 0.0076 1.0000 13.000 1.3323 0.02446 0.01840 0.0134 0.0073 1.0000 13.250 1.3433 0.02562 0.01960 0.0143 0.0071 1.0000 13.500 1.3534 0.02689 0.02092 0.0152 0.0068 1.0000 13.750 1.3621 0.02834 0.02243 0.0160 0.0066 1.0000 14.000 1.3687 0.03001 0.02416 0.0168 0.0063 1.0000 14.250 1.3767 0.03160 0.02583 0.0174 0.0062 1.0000 14.500 1.3844 0.03327 0.02757 0.0179 0.0061 1.0000 14.750 1.3908 0.03508 0.02946 0.0184 0.0060 1.0000 15.000 1.3961 0.03704 0.03149 0.0187 0.0058 1.0000 15.250 1.4004 0.03915 0.03368 0.0190 0.0057 1.0000 15.500 1.4032 0.04145 0.03606 0.0192 0.0056 1.0000 15.750 1.4048 0.04392 0.03861 0.0193 0.0055 1.0000 16.000 1.4051 0.04663 0.04139 0.0192 0.0053 1.0000 16.250 1.4042 0.04959 0.04444 0.0189 0.0052 1.0000 16.500 1.4017 0.05284 0.04778 0.0184 0.0051 1.0000 16.750 1.3975 0.05645 0.05148 0.0177 0.0051 1.0000 17.000 1.3917 0.06042 0.05555 0.0167 0.0050 1.0000 17.250 1.3838 0.06478 0.06001 0.0155 0.0049 1.0000 17.500 1.3734 0.06964 0.06499 0.0139 0.0048 1.0000 17.750 1.3610 0.07496 0.07043 0.0121 0.0048 1.0000 18.000 1.3461 0.08075 0.07634 0.0100 0.0048 1.0000 18.250 1.3293 0.08693 0.08264 0.0076 0.0047 1.0000 18.500 1.3111 0.09348 0.08931 0.0051 0.0047 1.0000 18.750 1.2921 0.10018 0.09613 0.0024 0.0047 1.0000 19.000 1.2723 0.10713 0.10320 -0.0005 0.0047 1.0000