XFOIL Version 6.96 Calculated polar for: ONERA OA209 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.6125 0.09393 0.09189 0.0152 1.0000 0.0188 -8.500 -0.6137 0.08753 0.08551 0.0087 1.0000 0.0193 -8.000 -0.6221 0.07009 0.06779 -0.0112 1.0000 0.0199 -7.750 -0.6165 0.06445 0.06195 -0.0139 1.0000 0.0200 -7.500 -0.6138 0.05862 0.05603 -0.0155 1.0000 0.0203 -7.250 -0.6012 0.05553 0.05289 -0.0165 1.0000 0.0205 -7.000 -0.5859 0.05283 0.05013 -0.0174 1.0000 0.0209 -6.750 -0.5690 0.04995 0.04715 -0.0184 1.0000 0.0215 -6.500 -0.5511 0.04657 0.04361 -0.0192 1.0000 0.0224 -6.250 -0.5278 0.04215 0.03853 -0.0186 1.0000 0.0246 -6.000 -0.5164 0.03661 0.03281 -0.0187 1.0000 0.0251 -5.750 -0.4936 0.03426 0.03039 -0.0195 0.9975 0.0256 -5.500 -0.4638 0.03203 0.02805 -0.0213 0.9947 0.0264 -5.250 -0.4335 0.02968 0.02548 -0.0225 0.9902 0.0282 -5.000 -0.4026 0.02601 0.02125 -0.0231 0.9851 0.0313 -4.750 -0.3761 0.02119 0.01587 -0.0217 0.9774 0.0240 -4.500 -0.3546 0.01889 0.01331 -0.0202 0.9688 0.0231 -4.250 -0.3334 0.01736 0.01153 -0.0182 0.9609 0.0233 -4.000 -0.3129 0.01589 0.00986 -0.0161 0.9532 0.0231 -3.750 -0.2897 0.01479 0.00861 -0.0147 0.9460 0.0235 -3.500 -0.2695 0.01410 0.00780 -0.0125 0.9391 0.0240 -3.250 -0.2441 0.01357 0.00718 -0.0116 0.9319 0.0247 -3.000 -0.2239 0.01253 0.00616 -0.0098 0.9255 0.0261 -2.750 -0.1980 0.01214 0.00578 -0.0092 0.9181 0.0279 -2.500 -0.1753 0.01169 0.00529 -0.0077 0.9114 0.0294 -2.250 -0.1492 0.01106 0.00463 -0.0071 0.9032 0.0310 -2.000 -0.1255 0.01060 0.00417 -0.0060 0.8959 0.0336 -1.750 -0.0977 0.01031 0.00387 -0.0058 0.8875 0.0370 -1.500 -0.0721 0.00985 0.00341 -0.0050 0.8803 0.0423 -1.250 -0.0437 0.00949 0.00307 -0.0049 0.8706 0.0504 -1.000 -0.0167 0.00914 0.00276 -0.0045 0.8612 0.0712 -0.750 0.0096 0.00643 0.00239 -0.0057 0.8507 0.7148 -0.500 0.0308 0.00616 0.00254 -0.0034 0.8378 0.8402 -0.250 0.0534 0.00622 0.00260 -0.0015 0.8226 0.8773 0.000 0.0756 0.00631 0.00264 0.0005 0.8049 0.9000 0.250 0.0973 0.00638 0.00264 0.0026 0.7840 0.9174 0.500 0.1169 0.00642 0.00259 0.0051 0.7583 0.9338 0.750 0.1325 0.00636 0.00244 0.0086 0.7281 0.9506 1.000 0.1497 0.00628 0.00221 0.0117 0.6891 0.9678 1.250 0.1773 0.00639 0.00206 0.0120 0.6300 0.9762 1.500 0.2089 0.00674 0.00202 0.0110 0.5403 0.9806 1.750 0.2412 0.00720 0.00205 0.0097 0.4470 0.9849 2.000 0.2762 0.00755 0.00213 0.0079 0.3949 0.9876 2.250 0.3109 0.00779 0.00220 0.0062 0.3652 0.9906 2.500 0.3454 0.00801 0.00229 0.0046 0.3440 0.9938 2.750 0.3810 0.00820 0.00239 0.0027 0.3259 0.9959 3.000 0.4165 0.00839 0.00249 0.0009 0.3105 0.9981 3.250 0.4481 0.00855 0.00258 -0.0001 0.2964 1.0000 3.500 0.4728 0.00866 0.00265 0.0003 0.2847 1.0000 3.750 0.4985 0.00880 0.00275 0.0005 0.2738 1.0000 4.000 0.5259 0.00898 0.00287 0.0004 0.2624 1.0000 4.250 0.5543 0.00916 0.00300 0.0000 0.2510 1.0000 4.500 0.5832 0.00933 0.00316 -0.0004 0.2406 1.0000 4.750 0.6124 0.00954 0.00332 -0.0009 0.2298 1.0000 5.000 0.6417 0.00977 0.00350 -0.0015 0.2191 1.0000 5.250 0.6712 0.00996 0.00369 -0.0020 0.2090 1.0000 5.500 0.7005 0.01019 0.00390 -0.0026 0.1989 1.0000 5.750 0.7297 0.01048 0.00412 -0.0031 0.1881 1.0000 6.000 0.7590 0.01068 0.00431 -0.0037 0.1769 1.0000 6.250 0.7881 0.01093 0.00456 -0.0042 0.1664 1.0000 6.500 0.8170 0.01122 0.00482 -0.0047 0.1566 1.0000 6.750 0.8458 0.01152 0.00508 -0.0052 0.1466 1.0000 7.000 0.8746 0.01179 0.00537 -0.0056 0.1376 1.0000 7.250 0.9030 0.01212 0.00568 -0.0061 0.1286 1.0000 7.500 0.9312 0.01247 0.00600 -0.0065 0.1192 1.0000 7.750 0.9595 0.01278 0.00634 -0.0069 0.1102 1.0000 8.000 0.9873 0.01315 0.00671 -0.0073 0.1009 1.0000 8.250 1.0148 0.01359 0.00711 -0.0076 0.0907 1.0000 8.500 1.0419 0.01406 0.00756 -0.0079 0.0793 1.0000 8.750 1.0686 0.01460 0.00806 -0.0081 0.0673 1.0000 9.000 1.0946 0.01525 0.00868 -0.0083 0.0565 1.0000 9.250 1.1198 0.01604 0.00944 -0.0084 0.0484 1.0000 9.500 1.1453 0.01668 0.01011 -0.0085 0.0435 1.0000 9.750 1.1694 0.01752 0.01100 -0.0084 0.0394 1.0000 10.000 1.1941 0.01819 0.01173 -0.0084 0.0367 1.0000 10.250 1.2161 0.01926 0.01283 -0.0082 0.0340 1.0000 10.500 1.2387 0.02013 0.01381 -0.0079 0.0325 1.0000 10.750 1.2614 0.02092 0.01470 -0.0076 0.0310 1.0000 11.000 1.2831 0.02176 0.01562 -0.0073 0.0295 1.0000 11.250 1.3012 0.02300 0.01691 -0.0067 0.0281 1.0000 11.500 1.3167 0.02447 0.01849 -0.0058 0.0270 1.0000 11.750 1.3357 0.02542 0.01957 -0.0052 0.0263 1.0000 12.000 1.3526 0.02652 0.02079 -0.0044 0.0255 1.0000 12.250 1.3676 0.02770 0.02208 -0.0034 0.0247 1.0000 12.500 1.3807 0.02893 0.02341 -0.0024 0.0240 1.0000 12.750 1.3893 0.03029 0.02485 -0.0009 0.0234 1.0000 13.000 1.3907 0.03213 0.02677 0.0010 0.0228 1.0000 13.250 1.3846 0.03492 0.02968 0.0030 0.0222 1.0000 13.500 1.3872 0.03700 0.03192 0.0040 0.0219 1.0000 13.750 1.3902 0.03915 0.03423 0.0045 0.0216 1.0000 14.000 1.3909 0.04172 0.03695 0.0047 0.0213 1.0000 14.250 1.3896 0.04473 0.04011 0.0044 0.0210 1.0000 14.500 1.3865 0.04818 0.04373 0.0035 0.0208 1.0000 14.750 1.3814 0.05218 0.04789 0.0019 0.0205 1.0000 15.000 1.3744 0.05675 0.05262 -0.0002 0.0203 1.0000 15.250 1.3656 0.06188 0.05791 -0.0030 0.0201 1.0000 15.500 1.3550 0.06756 0.06374 -0.0062 0.0199 1.0000 15.750 1.3427 0.07370 0.07003 -0.0098 0.0198 1.0000 16.000 1.3287 0.08024 0.07672 -0.0135 0.0197 1.0000 16.250 1.3129 0.08708 0.08369 -0.0173 0.0196 1.0000 16.500 1.2961 0.09419 0.09094 -0.0213 0.0195 1.0000 16.750 1.2783 0.10156 0.09844 -0.0254 0.0194 1.0000 17.000 1.2593 0.10930 0.10631 -0.0297 0.0193 1.0000 17.250 1.2395 0.11747 0.11462 -0.0343 0.0193 1.0000 17.500 1.2175 0.12636 0.12364 -0.0394 0.0193 1.0000 17.750 1.1910 0.13669 0.13413 -0.0455 0.0193 1.0000 18.000 1.1408 0.15358 0.15126 -0.0557 0.0197 1.0000