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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6382 0.19651 0.19414 0.0341 1.0000 0.0228 -16.500 -0.6303 0.19328 0.19090 0.0323 1.0000 0.0237 -16.250 -0.9102 0.11021 0.10740 -0.0057 1.0000 0.0156 -16.000 -0.9518 0.09847 0.09549 -0.0123 1.0000 0.0154 -15.750 -0.9891 0.08784 0.08471 -0.0184 1.0000 0.0152 -15.500 -1.0232 0.07785 0.07454 -0.0244 1.0000 0.0151 -15.250 -1.0538 0.06806 0.06458 -0.0308 1.0000 0.0150 -15.000 -1.0770 0.05847 0.05478 -0.0383 1.0000 0.0150 -14.750 -1.0938 0.05004 0.04611 -0.0460 1.0000 0.0150 -14.500 -1.1062 0.04492 0.04082 -0.0490 1.0000 0.0151 -14.250 -1.1150 0.04137 0.03711 -0.0494 1.0000 0.0152 -14.000 -1.1204 0.03864 0.03425 -0.0485 1.0000 0.0154 -13.750 -1.1231 0.03640 0.03189 -0.0470 1.0000 0.0156 -13.500 -1.1236 0.03449 0.02984 -0.0449 1.0000 0.0158 -13.250 -1.1224 0.03281 0.02802 -0.0425 1.0000 0.0161 -13.000 -1.1195 0.03131 0.02639 -0.0399 1.0000 0.0164 -12.750 -1.1149 0.03000 0.02494 -0.0371 1.0000 0.0167 -12.500 -1.1069 0.02887 0.02368 -0.0346 1.0000 0.0171 -12.250 -1.0935 0.02790 0.02256 -0.0329 1.0000 0.0174 -12.000 -1.0897 0.02601 0.02057 -0.0299 1.0000 0.0180 -11.750 -1.0762 0.02490 0.01940 -0.0282 1.0000 0.0186 -11.500 -1.0596 0.02398 0.01842 -0.0267 1.0000 0.0192 -11.250 -1.0421 0.02310 0.01744 -0.0254 1.0000 0.0199 -11.000 -1.0235 0.02225 0.01649 -0.0241 1.0000 0.0206 -10.750 -1.0033 0.02153 0.01565 -0.0230 1.0000 0.0213 -10.500 -0.9887 0.02026 0.01432 -0.0211 1.0000 0.0223 -10.250 -0.9688 0.01951 0.01353 -0.0200 1.0000 0.0234 -10.000 -0.9476 0.01889 0.01284 -0.0190 1.0000 0.0247 -9.750 -0.9258 0.01837 0.01224 -0.0180 1.0000 0.0260 -9.500 -0.9094 0.01747 0.01134 -0.0163 1.0000 0.0280 -9.250 -0.8867 0.01696 0.01079 -0.0156 0.9981 0.0302 -9.000 -0.8528 0.01611 0.00990 -0.0173 0.9907 0.0337 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0.1466 -4.000 -0.3146 0.01125 0.00428 -0.0131 0.7844 0.1512 -3.750 -0.2868 0.01118 0.00412 -0.0130 0.7794 0.1550 -3.500 -0.2598 0.01093 0.00390 -0.0129 0.7739 0.1606 -3.250 -0.2322 0.01077 0.00375 -0.0128 0.7683 0.1663 -3.000 -0.2044 0.01071 0.00361 -0.0126 0.7631 0.1713 -2.750 -0.1775 0.01046 0.00342 -0.0124 0.7559 0.1787 -2.500 -0.1503 0.01033 0.00325 -0.0122 0.7481 0.1857 -2.250 -0.1231 0.01014 0.00310 -0.0120 0.7407 0.1963 -2.000 -0.0958 0.00996 0.00298 -0.0119 0.7348 0.2112 -1.750 -0.0688 0.00980 0.00288 -0.0116 0.7297 0.2354 -1.500 -0.0420 0.00955 0.00281 -0.0115 0.7238 0.2746 -1.250 -0.0153 0.00932 0.00273 -0.0113 0.7182 0.3187 -1.000 0.0109 0.00910 0.00266 -0.0110 0.7129 0.3674 -0.750 0.0361 0.00874 0.00258 -0.0105 0.7067 0.4380 -0.500 0.0558 0.00801 0.00243 -0.0090 0.7009 0.5925 -0.250 0.0712 0.00728 0.00275 -0.0054 0.6954 0.8872 0.000 0.0989 0.00741 0.00289 -0.0048 0.6880 0.9130 0.250 0.1264 0.00757 0.00299 -0.0043 0.6802 0.9283 0.500 0.1528 0.00768 0.00309 -0.0035 0.6708 0.9403 0.750 0.1888 0.00791 0.00326 -0.0048 0.6624 0.9474 1.000 0.2183 0.00805 0.00337 -0.0048 0.6537 0.9557 1.250 0.2665 0.00830 0.00359 -0.0089 0.6443 0.9595 1.500 0.3102 0.00850 0.00372 -0.0121 0.6345 0.9636 1.750 0.3407 0.00860 0.00382 -0.0125 0.6237 0.9696 2.000 0.3973 0.00883 0.00400 -0.0184 0.6098 0.9734 2.250 0.4416 0.00901 0.00412 -0.0218 0.5918 0.9791 2.500 0.4848 0.00917 0.00419 -0.0251 0.5681 0.9843 2.750 0.5350 0.00932 0.00421 -0.0299 0.5377 0.9891 3.000 0.5749 0.00952 0.00428 -0.0326 0.5053 0.9938 3.250 0.6151 0.00966 0.00426 -0.0355 0.4685 0.9957 3.500 0.6537 0.00988 0.00430 -0.0381 0.4323 0.9981 3.750 0.6897 0.01013 0.00439 -0.0401 0.3992 1.0000 4.000 0.7151 0.01034 0.00449 -0.0399 0.3748 1.0000 4.250 0.7403 0.01056 0.00461 -0.0396 0.3545 1.0000 4.500 0.7653 0.01076 0.00474 -0.0393 0.3366 1.0000 4.750 0.7901 0.01096 0.00488 -0.0390 0.3202 1.0000 5.000 0.8146 0.01117 0.00503 -0.0386 0.3056 1.0000 5.250 0.8391 0.01137 0.00518 -0.0381 0.2925 1.0000 5.500 0.8634 0.01155 0.00534 -0.0376 0.2802 1.0000 5.750 0.8873 0.01175 0.00552 -0.0371 0.2688 1.0000 6.000 0.9109 0.01199 0.00571 -0.0365 0.2586 1.0000 6.250 0.9345 0.01218 0.00590 -0.0359 0.2492 1.0000 6.500 0.9577 0.01240 0.00610 -0.0352 0.2395 1.0000 6.750 0.9801 0.01267 0.00633 -0.0344 0.2291 1.0000 7.000 1.0029 0.01286 0.00653 -0.0337 0.2202 1.0000 7.250 1.0249 0.01312 0.00677 -0.0328 0.2119 1.0000 7.500 1.0466 0.01336 0.00701 -0.0319 0.2035 1.0000 7.750 1.0680 0.01361 0.00727 -0.0308 0.1965 1.0000 8.000 1.0885 0.01388 0.00753 -0.0297 0.1879 1.0000 8.250 1.1090 0.01414 0.00780 -0.0285 0.1802 1.0000 8.750 1.1470 0.01475 0.00840 -0.0257 0.1610 1.0000 9.000 1.1648 0.01509 0.00873 -0.0241 0.1508 1.0000 9.250 1.1811 0.01548 0.00908 -0.0223 0.1362 1.0000 9.500 1.1945 0.01601 0.00951 -0.0200 0.1160 1.0000 9.750 1.2042 0.01669 0.01005 -0.0171 0.0961 1.0000 10.000 1.2123 0.01736 0.01065 -0.0139 0.0848 1.0000 10.250 1.2201 0.01795 0.01124 -0.0106 0.0755 1.0000 10.500 1.2234 0.01868 0.01190 -0.0066 0.0595 1.0000 11.000 1.2047 0.02076 0.01372 0.0053 0.0280 1.0000 11.250 1.2087 0.02168 0.01468 0.0085 0.0253 1.0000 11.500 1.2122 0.02290 0.01595 0.0112 0.0230 1.0000 11.750 1.2216 0.02390 0.01703 0.0130 0.0218 1.0000 12.000 1.2296 0.02512 0.01832 0.0146 0.0208 1.0000 12.250 1.2356 0.02658 0.01985 0.0162 0.0199 1.0000 12.500 1.2375 0.02847 0.02182 0.0177 0.0191 1.0000 12.750 1.2401 0.03042 0.02387 0.0189 0.0185 1.0000 13.000 1.2460 0.03217 0.02572 0.0197 0.0180 1.0000 13.250 1.2501 0.03415 0.02781 0.0205 0.0176 1.0000 13.500 1.2528 0.03634 0.03009 0.0211 0.0171 1.0000 13.750 1.2541 0.03872 0.03255 0.0215 0.0166 1.0000 14.000 1.2534 0.04137 0.03529 0.0218 0.0163 1.0000 14.250 1.2502 0.04438 0.03839 0.0219 0.0159 1.0000 14.500 1.2435 0.04786 0.04196 0.0219 0.0156 1.0000 14.750 1.2333 0.05188 0.04608 0.0215 0.0153 1.0000 15.000 1.2216 0.05625 0.05055 0.0210 0.0151 1.0000 15.250 1.2206 0.05957 0.05398 0.0203 0.0149 1.0000 15.500 1.2177 0.06324 0.05776 0.0193 0.0147 1.0000 15.750 1.2137 0.06713 0.06175 0.0183 0.0145 1.0000 16.000 1.2090 0.07119 0.06592 0.0171 0.0144 1.0000 16.250 1.2041 0.07537 0.07020 0.0158 0.0142 1.0000 16.500 1.1991 0.07960 0.07452 0.0145 0.0140 1.0000 16.750 1.1940 0.08387 0.07889 0.0131 0.0138 1.0000