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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.9164 0.09116 0.08806 -0.0597 1.0000 0.0149 -17.250 -0.9938 0.07632 0.07300 -0.0683 1.0000 0.0142 -17.000 -1.1566 0.04869 0.04487 -0.0853 1.0000 0.0129 -16.750 -1.2018 0.03783 0.03373 -0.0939 1.0000 0.0128 -16.500 -1.2203 0.03288 0.02860 -0.0968 1.0000 0.0129 -16.250 -1.2316 0.02996 0.02556 -0.0968 1.0000 0.0131 -16.000 -1.2394 0.02799 0.02350 -0.0951 1.0000 0.0132 -15.750 -1.2460 0.02657 0.02199 -0.0923 1.0000 0.0134 -15.500 -1.2535 0.02551 0.02085 -0.0884 1.0000 0.0137 -15.250 -1.2565 0.02464 0.01991 -0.0846 0.9996 0.0139 -15.000 -1.2397 0.02344 0.01863 -0.0847 0.9973 0.0145 -14.750 -1.2198 0.02238 0.01751 -0.0849 0.9944 0.0152 -14.500 -1.1995 0.02141 0.01646 -0.0849 0.9916 0.0161 -14.250 -1.1781 0.02056 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0.1020 -4.250 -0.1255 0.00823 0.00213 -0.0796 0.7599 0.1090 -4.000 -0.0992 0.00815 0.00204 -0.0791 0.7509 0.1150 -3.750 -0.0737 0.00808 0.00196 -0.0785 0.7400 0.1215 -3.500 -0.0478 0.00804 0.00189 -0.0780 0.7267 0.1270 -3.250 -0.0224 0.00802 0.00183 -0.0773 0.7113 0.1311 -3.000 0.0026 0.00799 0.00177 -0.0766 0.6943 0.1366 -2.750 0.0279 0.00800 0.00172 -0.0759 0.6779 0.1411 -2.500 0.0534 0.00801 0.00168 -0.0752 0.6619 0.1437 -2.250 0.0785 0.00801 0.00163 -0.0745 0.6452 0.1477 -2.000 0.1033 0.00803 0.00160 -0.0737 0.6268 0.1517 -1.750 0.1283 0.00806 0.00157 -0.0730 0.6090 0.1553 -1.500 0.1535 0.00811 0.00155 -0.0723 0.5919 0.1582 -1.250 0.1790 0.00814 0.00153 -0.0717 0.5775 0.1611 -1.000 0.2044 0.00815 0.00152 -0.0710 0.5648 0.1668 -0.750 0.2301 0.00816 0.00151 -0.0705 0.5546 0.1717 -0.500 0.2564 0.00816 0.00151 -0.0700 0.5460 0.1763 -0.250 0.2821 0.00814 0.00150 -0.0694 0.5380 0.1857 0.000 0.3083 0.00813 0.00151 -0.0690 0.5311 0.1944 0.250 0.3341 0.00811 0.00152 -0.0684 0.5234 0.2071 0.500 0.3596 0.00810 0.00153 -0.0679 0.5161 0.2242 0.750 0.3851 0.00803 0.00155 -0.0673 0.5088 0.2521 1.000 0.4102 0.00800 0.00158 -0.0666 0.5022 0.2798 1.250 0.4360 0.00795 0.00161 -0.0661 0.4965 0.3039 1.500 0.4615 0.00792 0.00165 -0.0655 0.4899 0.3287 1.750 0.4862 0.00789 0.00170 -0.0648 0.4826 0.3595 2.000 0.5110 0.00787 0.00174 -0.0641 0.4712 0.3909 2.250 0.5347 0.00788 0.00180 -0.0632 0.4560 0.4265 2.500 0.5581 0.00788 0.00187 -0.0622 0.4405 0.4672 2.750 0.5807 0.00790 0.00194 -0.0611 0.4218 0.5104 3.000 0.6013 0.00797 0.00204 -0.0596 0.3944 0.5593 3.250 0.6196 0.00812 0.00218 -0.0577 0.3594 0.6149 3.500 0.6374 0.00816 0.00234 -0.0556 0.3365 0.6877 3.750 0.6546 0.00814 0.00248 -0.0533 0.3196 0.7679 4.000 0.6700 0.00809 0.00266 -0.0505 0.3024 0.8619 4.250 0.7246 0.00830 0.00298 -0.0564 0.2852 0.9490 4.500 0.7768 0.00857 0.00321 -0.0617 0.2717 0.9665 4.750 0.8142 0.00881 0.00339 -0.0639 0.2578 0.9746 5.000 0.8444 0.00911 0.00359 -0.0645 0.2396 0.9830 5.250 0.8777 0.00951 0.00385 -0.0659 0.2117 0.9908 5.750 0.9465 0.01044 0.00447 -0.0694 0.1590 1.0000 6.000 0.9620 0.01073 0.00469 -0.0669 0.1459 1.0000 6.250 0.9781 0.01100 0.00491 -0.0645 0.1341 1.0000 6.500 0.9930 0.01133 0.00516 -0.0620 0.1200 1.0000 6.750 1.0078 0.01166 0.00543 -0.0594 0.1066 1.0000 7.000 1.0232 0.01198 0.00568 -0.0570 0.0963 1.0000 7.250 1.0373 0.01225 0.00592 -0.0543 0.0890 1.0000 7.500 1.0497 0.01257 0.00619 -0.0513 0.0810 1.0000 7.750 1.0652 0.01282 0.00643 -0.0488 0.0766 1.0000 8.000 1.0793 0.01316 0.00673 -0.0463 0.0692 1.0000 8.250 1.0938 0.01353 0.00706 -0.0438 0.0611 1.0000 8.750 1.1182 0.01458 0.00795 -0.0384 0.0373 1.0000 9.000 1.1338 0.01499 0.00835 -0.0364 0.0342 1.0000 9.250 1.1500 0.01539 0.00876 -0.0345 0.0327 1.0000 9.500 1.1662 0.01581 0.00919 -0.0327 0.0315 1.0000 9.750 1.1814 0.01630 0.00968 -0.0307 0.0299 1.0000 10.000 1.1983 0.01671 0.01012 -0.0291 0.0294 1.0000 10.250 1.2146 0.01717 0.01060 -0.0274 0.0288 1.0000 10.500 1.2306 0.01766 0.01112 -0.0258 0.0283 1.0000 10.750 1.2460 0.01819 0.01168 -0.0242 0.0278 1.0000 11.000 1.2610 0.01877 0.01228 -0.0225 0.0273 1.0000 11.250 1.2754 0.01940 0.01293 -0.0209 0.0268 1.0000 11.500 1.2890 0.02009 0.01365 -0.0192 0.0262 1.0000 11.750 1.3016 0.02086 0.01445 -0.0175 0.0256 1.0000 12.000 1.3151 0.02161 0.01524 -0.0159 0.0253 1.0000 12.250 1.3293 0.02233 0.01600 -0.0146 0.0250 1.0000 12.500 1.3424 0.02314 0.01685 -0.0131 0.0247 1.0000 12.750 1.3555 0.02397 0.01772 -0.0118 0.0243 1.0000 13.000 1.3680 0.02487 0.01867 -0.0105 0.0240 1.0000 13.250 1.3800 0.02582 0.01967 -0.0092 0.0236 1.0000 13.500 1.3906 0.02691 0.02080 -0.0080 0.0233 1.0000 13.750 1.4011 0.02804 0.02197 -0.0068 0.0228 1.0000 14.000 1.4103 0.02930 0.02327 -0.0056 0.0225 1.0000 14.250 1.4186 0.03066 0.02469 -0.0044 0.0223 1.0000 14.500 1.4250 0.03223 0.02631 -0.0033 0.0218 1.0000 14.750 1.4295 0.03403 0.02817 -0.0023 0.0214 1.0000 15.000 1.4380 0.03553 0.02972 -0.0015 0.0213 1.0000 15.250 1.4463 0.03709 0.03134 -0.0008 0.0210 1.0000 15.500 1.4529 0.03885 0.03318 -0.0002 0.0208 1.0000 15.750 1.4603 0.04059 0.03497 0.0003 0.0205 1.0000 16.000 1.4652 0.04262 0.03708 0.0007 0.0203 1.0000 16.250 1.4713 0.04456 0.03908 0.0010 0.0199 1.0000 16.500 1.4754 0.04680 0.04138 0.0013 0.0196 1.0000 16.750 1.4779 0.04925 0.04390 0.0014 0.0194 1.0000 17.000 1.4801 0.05179 0.04651 0.0014 0.0192 1.0000 17.250 1.4815 0.05445 0.04923 0.0013 0.0189 1.0000 17.500 1.4812 0.05739 0.05225 0.0010 0.0187 1.0000 17.750 1.4799 0.06051 0.05543 0.0007 0.0183 1.0000 18.000 1.4751 0.06412 0.05911 0.0001 0.0180 1.0000 18.250 1.4694 0.06788 0.06296 -0.0006 0.0180 1.0000 18.500 1.4697 0.07091 0.06608 -0.0011 0.0177 1.0000 18.750 1.4647 0.07471 0.06997 -0.0020 0.0176 1.0000 19.000 1.4636 0.07801 0.07334 -0.0027 0.0173 1.0000 19.250 1.4582 0.08191 0.07733 -0.0037 0.0171 1.0000