XFOIL Version 6.96 Calculated polar for: GOE 723 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 ------ -------- --------- --------- -------- -------- -------- -12.500 -0.4053 0.11743 0.11555 -0.0360 1.0000 0.0161 -12.250 -0.4008 0.11463 0.11276 -0.0368 1.0000 0.0162 -11.750 -0.7206 0.03733 0.03484 -0.0950 0.9893 0.0195 -11.500 -0.7071 0.03222 0.02946 -0.1036 0.9799 0.0196 -11.250 -0.6905 0.02981 0.02689 -0.1060 0.9693 0.0197 -11.000 -0.6647 0.02797 0.02491 -0.1088 0.9583 0.0198 -10.750 -0.6270 0.02633 0.02313 -0.1134 0.9473 0.0200 -10.500 -0.5809 0.02443 0.02103 -0.1198 0.9353 0.0201 -10.250 -0.5358 0.02323 0.01964 -0.1251 0.9151 0.0203 -10.000 -0.5098 0.02217 0.01835 -0.1262 0.8887 0.0205 -9.750 -0.4894 0.02147 0.01746 -0.1256 0.8671 0.0207 -9.500 -0.4717 0.02050 0.01628 -0.1245 0.8474 0.0208 -9.250 -0.4528 0.01964 0.01524 -0.1235 0.8302 0.0210 -9.000 -0.4334 0.01880 0.01422 -0.1225 0.8142 0.0211 -8.750 -0.4135 0.01797 0.01321 -0.1215 0.7989 0.0213 -8.500 -0.3927 0.01722 0.01229 -0.1206 0.7841 0.0215 -8.250 -0.3709 0.01654 0.01146 -0.1197 0.7716 0.0216 -8.000 -0.3489 0.01586 0.01063 -0.1189 0.7605 0.0218 -7.750 -0.3262 0.01526 0.00990 -0.1181 0.7497 0.0219 -7.500 -0.3028 0.01471 0.00923 -0.1173 0.7398 0.0221 -7.250 -0.2794 0.01421 0.00860 -0.1166 0.7305 0.0223 -7.000 -0.2551 0.01372 0.00802 -0.1160 0.7223 0.0224 -6.500 -0.2059 0.01291 0.00704 -0.1148 0.7073 0.0227 -6.250 -0.1806 0.01265 0.00669 -0.1142 0.6995 0.0229 -6.000 -0.1548 0.01240 0.00638 -0.1137 0.6928 0.0230 -5.750 -0.1304 0.01190 0.00581 -0.1131 0.6861 0.0232 -5.500 -0.1064 0.01140 0.00523 -0.1124 0.6800 0.0234 -5.250 -0.0812 0.01102 0.00482 -0.1118 0.6740 0.0237 -5.000 -0.0557 0.01075 0.00450 -0.1113 0.6672 0.0239 -4.750 -0.0300 0.01050 0.00421 -0.1108 0.6613 0.0241 -4.500 -0.0038 0.01027 0.00395 -0.1103 0.6552 0.0243 -4.250 0.0223 0.01008 0.00372 -0.1099 0.6493 0.0246 -4.000 0.0484 0.00987 0.00347 -0.1094 0.6439 0.0248 -3.750 0.0748 0.00968 0.00325 -0.1090 0.6378 0.0250 -3.500 0.1010 0.00952 0.00304 -0.1085 0.6316 0.0253 -3.250 0.1275 0.00935 0.00285 -0.1081 0.6264 0.0256 -3.000 0.1541 0.00920 0.00266 -0.1078 0.6207 0.0258 -2.750 0.1805 0.00907 0.00249 -0.1073 0.6146 0.0261 -2.500 0.2073 0.00894 0.00233 -0.1069 0.6092 0.0265 -2.250 0.2339 0.00883 0.00219 -0.1065 0.6020 0.0268 -2.000 0.2604 0.00876 0.00207 -0.1061 0.5940 0.0271 -1.750 0.2870 0.00870 0.00198 -0.1057 0.5843 0.0275 -1.500 0.3133 0.00859 0.00183 -0.1052 0.5768 0.0280 -1.250 0.3400 0.00849 0.00170 -0.1048 0.5697 0.0287 -1.000 0.3665 0.00843 0.00162 -0.1044 0.5640 0.0293 -0.750 0.3937 0.00837 0.00155 -0.1041 0.5585 0.0300 -0.500 0.4205 0.00833 0.00150 -0.1037 0.5520 0.0307 -0.250 0.4473 0.00831 0.00145 -0.1034 0.5467 0.0315 0.000 0.4744 0.00827 0.00142 -0.1031 0.5415 0.0323 0.250 0.5011 0.00827 0.00139 -0.1027 0.5340 0.0336 0.500 0.5277 0.00826 0.00137 -0.1023 0.5269 0.0364 0.750 0.5540 0.00823 0.00136 -0.1018 0.5178 0.0482 1.000 0.5778 0.00782 0.00134 -0.1011 0.5101 0.2031 1.250 0.6027 0.00771 0.00138 -0.1005 0.4995 0.2703 1.500 0.6287 0.00765 0.00143 -0.1000 0.4910 0.3174 1.750 0.6545 0.00768 0.00149 -0.0995 0.4823 0.3455 2.000 0.6806 0.00769 0.00156 -0.0990 0.4723 0.3736 2.250 0.7062 0.00774 0.00163 -0.0985 0.4613 0.3989 2.500 0.7313 0.00781 0.00171 -0.0979 0.4472 0.4251 2.750 0.7561 0.00789 0.00181 -0.0972 0.4324 0.4542 3.000 0.7805 0.00798 0.00192 -0.0964 0.4155 0.4862 3.250 0.8037 0.00811 0.00207 -0.0955 0.3926 0.5308 3.500 0.8260 0.00833 0.00224 -0.0943 0.3656 0.5634 3.750 0.8481 0.00853 0.00242 -0.0932 0.3417 0.5995 4.250 0.9587 0.00856 0.00304 -0.1061 0.2895 0.9984 4.500 0.9869 0.00888 0.00325 -0.1063 0.2679 1.0000 4.750 1.0073 0.00931 0.00351 -0.1049 0.2366 1.0000 5.000 1.0127 0.01065 0.00428 -0.1009 0.1269 1.0000 5.250 1.0322 0.01111 0.00461 -0.0994 0.1037 1.0000 5.500 1.0538 0.01144 0.00488 -0.0981 0.0895 1.0000 5.750 1.0720 0.01196 0.00524 -0.0964 0.0642 1.0000 6.000 1.0938 0.01225 0.00550 -0.0952 0.0590 1.0000 6.250 1.1154 0.01254 0.00577 -0.0941 0.0551 1.0000 6.500 1.1375 0.01280 0.00603 -0.0929 0.0530 1.0000 6.750 1.1594 0.01306 0.00629 -0.0918 0.0518 1.0000 7.000 1.1808 0.01333 0.00657 -0.0906 0.0504 1.0000 7.250 1.2014 0.01364 0.00687 -0.0893 0.0488 1.0000 7.500 1.2214 0.01396 0.00720 -0.0879 0.0474 1.0000 7.750 1.2409 0.01430 0.00755 -0.0864 0.0460 1.0000 8.000 1.2592 0.01468 0.00794 -0.0847 0.0447 1.0000 8.250 1.2773 0.01497 0.00825 -0.0829 0.0444 1.0000 8.500 1.2950 0.01525 0.00856 -0.0811 0.0434 1.0000 8.750 1.3120 0.01557 0.00889 -0.0792 0.0426 1.0000 9.000 1.3288 0.01591 0.00925 -0.0773 0.0413 1.0000 9.250 1.3449 0.01631 0.00966 -0.0754 0.0403 1.0000 9.500 1.3605 0.01675 0.01011 -0.0734 0.0390 1.0000 9.750 1.3748 0.01727 0.01064 -0.0713 0.0376 1.0000 10.000 1.3909 0.01772 0.01112 -0.0696 0.0371 1.0000 10.250 1.4075 0.01816 0.01160 -0.0680 0.0364 1.0000 10.500 1.4231 0.01867 0.01215 -0.0664 0.0357 1.0000 10.750 1.4382 0.01922 0.01273 -0.0647 0.0347 1.0000 11.000 1.4525 0.01984 0.01337 -0.0631 0.0336 1.0000 11.250 1.4661 0.02054 0.01409 -0.0614 0.0327 1.0000 11.500 1.4784 0.02134 0.01490 -0.0597 0.0314 1.0000 11.750 1.4922 0.02208 0.01570 -0.0583 0.0308 1.0000 12.000 1.5053 0.02290 0.01656 -0.0569 0.0299 1.0000 12.250 1.5177 0.02379 0.01749 -0.0555 0.0287 1.0000 12.500 1.5291 0.02480 0.01852 -0.0542 0.0275 1.0000 12.750 1.5397 0.02591 0.01966 -0.0528 0.0263 1.0000 13.000 1.5506 0.02703 0.02082 -0.0516 0.0249 1.0000 13.250 1.5602 0.02829 0.02211 -0.0504 0.0233 1.0000 13.500 1.5685 0.02971 0.02355 -0.0492 0.0219 1.0000 13.750 1.5766 0.03117 0.02506 -0.0481 0.0205 1.0000 14.000 1.5828 0.03283 0.02676 -0.0471 0.0191 1.0000 14.250 1.5887 0.03459 0.02855 -0.0461 0.0180 1.0000 14.500 1.5939 0.03642 0.03044 -0.0451 0.0169 1.0000 14.750 1.5975 0.03845 0.03251 -0.0442 0.0158 1.0000 15.000 1.6002 0.04061 0.03472 -0.0433 0.0149 1.0000 15.250 1.6044 0.04268 0.03686 -0.0426 0.0146 1.0000 15.500 1.6070 0.04493 0.03917 -0.0420 0.0140 1.0000 15.750 1.6087 0.04734 0.04165 -0.0414 0.0135 1.0000 16.000 1.6089 0.04998 0.04434 -0.0409 0.0128 1.0000 16.250 1.6086 0.05271 0.04714 -0.0405 0.0123 1.0000 16.500 1.6093 0.05538 0.04988 -0.0402 0.0121 1.0000 16.750 1.6107 0.05803 0.05261 -0.0400 0.0118 1.0000 17.000 1.6109 0.06087 0.05552 -0.0399 0.0115 1.0000 17.250 1.6100 0.06389 0.05862 -0.0398 0.0112 1.0000 17.500 1.6087 0.06698 0.06179 -0.0399 0.0110 1.0000 17.750 1.6067 0.07021 0.06510 -0.0401 0.0107 1.0000 18.000 1.6040 0.07359 0.06855 -0.0403 0.0104 1.0000 18.250 1.6008 0.07708 0.07211 -0.0407 0.0102 1.0000 18.500 1.5960 0.08081 0.07592 -0.0411 0.0100 1.0000 18.750 1.5906 0.08469 0.07988 -0.0417 0.0098 1.0000