XFOIL Version 6.96 Calculated polar for: GOE 703 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0395 0.07966 0.07579 -0.0760 1.0000 0.0286 -19.500 -1.0481 0.07534 0.07138 -0.0779 1.0000 0.0286 -19.250 -1.0560 0.07115 0.06710 -0.0797 1.0000 0.0288 -19.000 -1.0625 0.06720 0.06305 -0.0813 1.0000 0.0289 -18.750 -1.0689 0.06344 0.05921 -0.0826 1.0000 0.0289 -18.500 -1.0732 0.05999 0.05567 -0.0837 1.0000 0.0291 -18.250 -1.0774 0.05667 0.05227 -0.0846 1.0000 0.0292 -18.000 -1.0802 0.05367 0.04918 -0.0852 1.0000 0.0293 -17.750 -1.0822 0.05083 0.04626 -0.0856 1.0000 0.0294 -17.500 -1.0840 0.04814 0.04350 -0.0857 1.0000 0.0294 -17.250 -1.0839 0.04575 0.04103 -0.0855 1.0000 0.0295 -17.000 -1.0829 0.04357 0.03877 -0.0852 1.0000 0.0297 -16.750 -1.0820 0.04149 0.03662 -0.0846 1.0000 0.0298 -16.500 -1.0804 0.03957 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0.00264 -0.0408 0.5701 0.3839 -2.000 0.0329 0.00810 0.00251 -0.0359 0.5669 0.4625 -1.750 0.0365 0.00774 0.00240 -0.0308 0.5631 0.5290 -1.500 0.0349 0.00742 0.00230 -0.0245 0.5592 0.5886 -1.250 0.0279 0.00714 0.00223 -0.0169 0.5549 0.6480 -1.000 0.0173 0.00696 0.00222 -0.0084 0.5506 0.7012 -0.750 0.0158 0.00681 0.00224 -0.0018 0.5475 0.7467 -0.500 0.0273 0.00671 0.00227 0.0019 0.5441 0.7807 -0.250 0.0433 0.00669 0.00231 0.0047 0.5399 0.8053 0.000 0.0619 0.00671 0.00235 0.0069 0.5354 0.8228 0.250 0.0830 0.00678 0.00241 0.0085 0.5301 0.8353 0.500 0.0998 0.00679 0.00243 0.0111 0.5271 0.8467 0.750 0.1283 0.00683 0.00250 0.0110 0.5231 0.8555 1.000 0.1399 0.00685 0.00250 0.0147 0.5189 0.8646 1.250 0.1715 0.00697 0.00261 0.0140 0.5135 0.8718 1.500 0.1799 0.00702 0.00264 0.0184 0.5093 0.8808 1.750 0.2122 0.00709 0.00273 0.0175 0.5056 0.8863 2.000 0.2365 0.00718 0.00282 0.0184 0.5000 0.8920 2.250 0.2363 0.00720 0.00281 0.0247 0.4947 0.9001 2.500 0.2752 0.00737 0.00297 0.0223 0.4888 0.9040 2.750 0.3085 0.00753 0.00314 0.0212 0.4832 0.9087 3.000 0.3167 0.00761 0.00321 0.0256 0.4786 0.9163 3.250 0.3487 0.00783 0.00339 0.0248 0.4727 0.9203 3.500 0.3901 0.00801 0.00359 0.0219 0.4672 0.9223 3.750 0.4249 0.00820 0.00375 0.0203 0.4602 0.9243 4.000 0.4552 0.00843 0.00394 0.0197 0.4533 0.9271 4.250 0.4508 0.00841 0.00394 0.0268 0.4494 0.9352 4.500 0.4917 0.00863 0.00414 0.0239 0.4418 0.9363 4.750 0.5269 0.00885 0.00431 0.0221 0.4331 0.9372 5.000 0.5624 0.00901 0.00445 0.0203 0.4238 0.9378 5.250 0.5945 0.00921 0.00460 0.0191 0.4147 0.9386 5.500 0.6257 0.00938 0.00475 0.0182 0.4054 0.9396 5.750 0.6545 0.00960 0.00493 0.0178 0.3971 0.9409 6.000 0.6828 0.00976 0.00508 0.0175 0.3891 0.9424 6.250 0.6692 0.00978 0.00509 0.0261 0.3839 0.9511 6.500 0.7024 0.00998 0.00526 0.0246 0.3748 0.9517 7.000 0.7636 0.01046 0.00568 0.0227 0.3559 0.9531 7.500 0.8202 0.01098 0.00615 0.0216 0.3381 0.9547 7.750 0.8461 0.01132 0.00644 0.0215 0.3282 0.9558 8.000 0.8736 0.01157 0.00667 0.0211 0.3194 0.9571 8.250 0.8954 0.01191 0.00698 0.0217 0.3107 0.9591 8.500 0.8935 0.01207 0.00715 0.0275 0.3055 0.9660 8.750 0.9208 0.01242 0.00747 0.0268 0.2959 0.9667 9.000 0.9492 0.01274 0.00777 0.0260 0.2867 0.9674 9.250 0.9748 0.01320 0.00817 0.0256 0.2742 0.9683 9.500 0.9991 0.01367 0.00860 0.0253 0.2621 0.9693 9.750 1.0212 0.01419 0.00907 0.0254 0.2479 0.9707 10.000 1.0402 0.01479 0.00961 0.0259 0.2332 0.9724 10.250 1.0548 0.01550 0.01025 0.0271 0.2179 0.9750 10.500 1.0557 0.01634 0.01103 0.0309 0.2029 0.9801 10.750 1.0737 0.01731 0.01190 0.0308 0.1853 0.9810 11.000 1.0917 0.01826 0.01279 0.0307 0.1717 0.9819 11.250 1.1101 0.01916 0.01366 0.0305 0.1620 0.9830 11.500 1.1271 0.02014 0.01461 0.0305 0.1534 0.9843 11.750 1.1441 0.02109 0.01554 0.0304 0.1471 0.9857 12.000 1.1606 0.02208 0.01654 0.0305 0.1423 0.9875 12.250 1.1778 0.02296 0.01744 0.0306 0.1386 0.9893 12.500 1.1898 0.02403 0.01851 0.0314 0.1356 0.9915 12.750 1.2029 0.02520 0.01969 0.0317 0.1319 0.9928 13.000 1.2220 0.02618 0.02071 0.0310 0.1295 0.9936 13.250 1.2403 0.02721 0.02177 0.0305 0.1265 0.9945 13.500 1.2561 0.02843 0.02299 0.0300 0.1235 0.9956 13.750 1.2694 0.02993 0.02451 0.0295 0.1200 0.9969 14.000 1.2870 0.03111 0.02573 0.0288 0.1176 0.9980 14.250 1.3030 0.03243 0.02709 0.0282 0.1146 0.9989 14.500 1.3149 0.03413 0.02879 0.0277 0.1110 0.9997 14.750 1.3203 0.03570 0.03039 0.0285 0.1077 1.0000 15.000 1.3226 0.03707 0.03180 0.0303 0.1044 1.0000 15.250 1.3186 0.03899 0.03371 0.0323 0.1000 1.0000 15.500 1.3193 0.04059 0.03534 0.0339 0.0956 1.0000 15.750 1.3147 0.04267 0.03740 0.0356 0.0883 1.0000 16.000 1.3066 0.04513 0.03983 0.0373 0.0782 1.0000 16.250 1.2941 0.04809 0.04274 0.0390 0.0695 1.0000 16.500 1.2840 0.05093 0.04557 0.0404 0.0649 1.0000 16.750 1.2776 0.05350 0.04817 0.0415 0.0624 1.0000 17.000 1.2703 0.05628 0.05097 0.0425 0.0601 1.0000 17.250 1.2675 0.05869 0.05344 0.0433 0.0590 1.0000 17.500 1.2650 0.06111 0.05590 0.0440 0.0580 1.0000 17.750 1.2590 0.06397 0.05881 0.0446 0.0569 1.0000 18.000 1.2534 0.06686 0.06174 0.0450 0.0558 1.0000 18.250 1.2457 0.07005 0.06498 0.0453 0.0545 1.0000 18.500 1.2443 0.07261 0.06760 0.0456 0.0539 1.0000 18.750 1.2428 0.07519 0.07024 0.0458 0.0532 1.0000 19.000 1.2402 0.07796 0.07307 0.0458 0.0525 1.0000 19.250 1.2372 0.08081 0.07597 0.0458 0.0518 1.0000