XFOIL Version 6.96 Calculated polar for: GOE 629 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 -0.9816 0.08165 0.07854 -0.0654 1.0000 0.0205 -17.250 -1.0824 0.06383 0.06047 -0.0758 1.0000 0.0196 -17.000 -1.1800 0.04543 0.04171 -0.0878 1.0000 0.0185 -16.750 -1.2139 0.03663 0.03266 -0.0948 1.0000 0.0185 -16.500 -1.2318 0.03203 0.02791 -0.0971 1.0000 0.0187 -16.250 -1.2433 0.02927 0.02503 -0.0967 1.0000 0.0190 -16.000 -1.2514 0.02740 0.02306 -0.0947 1.0000 0.0192 -15.750 -1.2585 0.02603 0.02160 -0.0916 1.0000 0.0196 -15.500 -1.2663 0.02504 0.02054 -0.0873 1.0000 0.0199 -15.250 -1.2812 0.02432 0.01975 -0.0811 1.0000 0.0202 -15.000 -1.2966 0.02361 0.01897 -0.0745 1.0000 0.0206 -14.750 -1.3022 0.02275 0.01806 -0.0697 1.0000 0.0212 -14.500 -1.2800 0.02167 0.01691 -0.0701 0.9986 0.0225 -14.250 -1.2540 0.02070 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0.250 0.3391 0.00709 0.00147 -0.0700 0.6122 0.3460 0.500 0.3628 0.00704 0.00149 -0.0691 0.5990 0.3844 0.750 0.3863 0.00696 0.00152 -0.0681 0.5863 0.4355 1.000 0.4095 0.00683 0.00156 -0.0671 0.5757 0.4962 1.250 0.4314 0.00672 0.00161 -0.0658 0.5658 0.5646 1.500 0.4532 0.00652 0.00165 -0.0644 0.5572 0.6450 1.750 0.4716 0.00633 0.00173 -0.0622 0.5488 0.7429 2.000 0.4919 0.00617 0.00181 -0.0604 0.5405 0.8216 2.250 0.5159 0.00612 0.00193 -0.0592 0.5307 0.8902 2.500 0.5545 0.00622 0.00208 -0.0613 0.5183 0.9357 2.750 0.5986 0.00638 0.00221 -0.0648 0.5052 0.9546 3.000 0.6383 0.00656 0.00233 -0.0673 0.4906 0.9652 3.250 0.6766 0.00674 0.00246 -0.0695 0.4782 0.9726 3.500 0.7089 0.00694 0.00259 -0.0703 0.4616 0.9805 3.750 0.7483 0.00715 0.00272 -0.0728 0.4387 0.9847 4.000 0.7848 0.00743 0.00286 -0.0747 0.4099 0.9890 4.250 0.8176 0.00775 0.00303 -0.0759 0.3802 0.9932 4.500 0.8584 0.00806 0.00321 -0.0788 0.3533 0.9966 4.750 0.8969 0.00837 0.00340 -0.0813 0.3310 0.9994 5.250 0.9390 0.00879 0.00369 -0.0786 0.3019 1.0000 5.500 0.9573 0.00896 0.00383 -0.0766 0.2911 1.0000 5.750 0.9747 0.00917 0.00398 -0.0745 0.2787 1.0000 6.250 1.0088 0.00964 0.00433 -0.0701 0.2495 1.0000 6.500 1.0249 0.00992 0.00452 -0.0677 0.2297 1.0000 6.750 1.0389 0.01029 0.00477 -0.0650 0.2051 1.0000 7.000 1.0517 0.01072 0.00505 -0.0621 0.1803 1.0000 7.250 1.0644 0.01115 0.00537 -0.0592 0.1602 1.0000 7.750 1.0886 0.01191 0.00597 -0.0530 0.1298 1.0000 8.250 1.1132 0.01266 0.00658 -0.0471 0.1046 1.0000 8.500 1.1268 0.01306 0.00693 -0.0445 0.0938 1.0000 8.750 1.1406 0.01349 0.00730 -0.0420 0.0835 1.0000 9.000 1.1541 0.01396 0.00772 -0.0395 0.0728 1.0000 9.250 1.1650 0.01458 0.00823 -0.0367 0.0558 1.0000 9.500 1.1748 0.01529 0.00883 -0.0338 0.0427 1.0000 9.750 1.1884 0.01585 0.00937 -0.0316 0.0385 1.0000 10.000 1.2022 0.01641 0.00993 -0.0295 0.0362 1.0000 10.250 1.2165 0.01697 0.01051 -0.0275 0.0347 1.0000 10.500 1.2319 0.01749 0.01106 -0.0257 0.0338 1.0000 10.750 1.2465 0.01807 0.01167 -0.0239 0.0330 1.0000 11.000 1.2601 0.01872 0.01235 -0.0221 0.0321 1.0000 11.250 1.2716 0.01951 0.01316 -0.0200 0.0310 1.0000 11.500 1.2817 0.02042 0.01411 -0.0179 0.0302 1.0000 11.750 1.2958 0.02110 0.01484 -0.0164 0.0298 1.0000 12.000 1.3089 0.02188 0.01567 -0.0148 0.0294 1.0000 12.250 1.3213 0.02272 0.01656 -0.0133 0.0289 1.0000 12.500 1.3330 0.02363 0.01751 -0.0118 0.0284 1.0000 12.750 1.3436 0.02465 0.01858 -0.0102 0.0279 1.0000 13.000 1.3536 0.02574 0.01971 -0.0088 0.0274 1.0000 13.250 1.3610 0.02706 0.02108 -0.0072 0.0269 1.0000 13.500 1.3655 0.02866 0.02273 -0.0056 0.0264 1.0000 13.750 1.3657 0.03064 0.02479 -0.0039 0.0259 1.0000 14.000 1.3741 0.03206 0.02627 -0.0029 0.0256 1.0000 14.250 1.3837 0.03342 0.02769 -0.0020 0.0253 1.0000 14.500 1.3910 0.03501 0.02935 -0.0011 0.0251 1.0000 14.750 1.3980 0.03668 0.03109 -0.0004 0.0247 1.0000 15.000 1.4034 0.03856 0.03303 0.0003 0.0244 1.0000 15.250 1.4083 0.04055 0.03509 0.0009 0.0240 1.0000 15.500 1.4118 0.04275 0.03735 0.0013 0.0237 1.0000 15.750 1.4141 0.04513 0.03979 0.0017 0.0234 1.0000 16.000 1.4158 0.04765 0.04237 0.0018 0.0231 1.0000 16.250 1.4162 0.05039 0.04517 0.0019 0.0227 1.0000 16.500 1.4117 0.05373 0.04858 0.0018 0.0224 1.0000 16.750 1.4034 0.05758 0.05253 0.0015 0.0222 1.0000 17.000 1.3942 0.06162 0.05665 0.0011 0.0220 1.0000 17.250 1.4011 0.06388 0.05899 0.0007 0.0217 1.0000 17.500 1.4003 0.06704 0.06223 0.0002 0.0215 1.0000 17.750 1.3987 0.07036 0.06563 -0.0004 0.0214 1.0000 18.000 1.3979 0.07365 0.06901 -0.0011 0.0211 1.0000 18.250 1.3941 0.07736 0.07280 -0.0020 0.0209 1.0000 18.500 1.3911 0.08100 0.07652 -0.0029 0.0207 1.0000 18.750 1.3874 0.08478 0.08038 -0.0039 0.0204 1.0000 19.000 1.3839 0.08860 0.08428 -0.0051 0.0201 1.0000 19.250 1.3794 0.09261 0.08836 -0.0063 0.0199 1.0000