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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.6750 0.12678 0.12524 0.0402 0.9698 0.0058 -10.750 -0.6731 0.12290 0.12136 0.0387 0.9664 0.0058 -8.750 -0.8895 0.02233 0.01819 0.0006 0.9313 0.0072 -8.500 -0.8674 0.02047 0.01603 0.0011 0.9291 0.0074 -8.250 -0.8437 0.01919 0.01455 0.0015 0.9270 0.0075 -8.000 -0.8193 0.01819 0.01338 0.0020 0.9250 0.0076 -7.750 -0.7943 0.01681 0.01180 0.0021 0.9229 0.0078 -7.500 -0.7679 0.01603 0.01092 0.0022 0.9206 0.0080 -7.250 -0.7412 0.01543 0.01026 0.0022 0.9181 0.0081 -7.000 -0.7144 0.01488 0.00964 0.0023 0.9156 0.0083 -6.750 -0.6877 0.01436 0.00904 0.0025 0.9132 0.0085 -6.500 -0.6611 0.01390 0.00851 0.0027 0.9109 0.0087 -6.250 -0.6336 0.01337 0.00792 0.0027 0.9083 0.0089 -6.000 -0.6058 0.01286 0.00735 0.0027 0.9053 0.0091 -5.750 -0.5781 0.01239 0.00682 0.0027 0.9021 0.0094 -5.500 -0.5509 0.01195 0.00631 0.0029 0.8982 0.0097 -5.250 -0.5236 0.01156 0.00586 0.0031 0.8932 0.0099 -5.000 -0.4956 0.01112 0.00537 0.0030 0.8864 0.0103 -4.750 -0.4684 0.01077 0.00498 0.0032 0.8804 0.0107 -4.500 -0.4399 0.01050 0.00471 0.0031 0.8736 0.0112 -4.250 -0.4119 0.01022 0.00439 0.0031 0.8662 0.0116 -4.000 -0.3835 0.00993 0.00407 0.0031 0.8581 0.0121 -3.750 -0.3554 0.00967 0.00375 0.0031 0.8487 0.0125 -3.500 -0.3267 0.00944 0.00347 0.0031 0.8371 0.0128 -3.250 -0.2982 0.00915 0.00315 0.0030 0.8243 0.0136 -3.000 -0.2695 0.00898 0.00293 0.0029 0.8092 0.0144 -2.750 -0.2406 0.00884 0.00273 0.0028 0.7894 0.0153 -2.500 -0.2115 0.00874 0.00253 0.0026 0.7664 0.0162 -2.250 -0.1820 0.00860 0.00232 0.0023 0.7419 0.0177 -2.000 -0.1524 0.00852 0.00216 0.0020 0.7173 0.0191 -1.750 -0.1226 0.00847 0.00201 0.0016 0.6870 0.0207 -1.500 -0.0925 0.00845 0.00188 0.0011 0.6495 0.0233 -1.250 -0.0623 0.00848 0.00178 0.0005 0.6053 0.0269 -1.000 -0.0318 0.00858 0.00169 -0.0002 0.5466 0.0316 -0.750 -0.0013 0.00871 0.00163 -0.0009 0.4794 0.0396 -0.500 0.0292 0.00886 0.00160 -0.0017 0.4122 0.0552 -0.250 0.0592 0.00887 0.00157 -0.0023 0.3774 0.0836 0.000 0.0900 0.00803 0.00147 -0.0037 0.3541 0.3572 0.250 0.1211 0.00701 0.00139 -0.0052 0.3354 0.6666 0.500 0.1503 0.00676 0.00145 -0.0056 0.3205 0.7728 0.750 0.1787 0.00674 0.00153 -0.0056 0.3070 0.8254 1.000 0.2066 0.00681 0.00163 -0.0054 0.2954 0.8589 1.250 0.2345 0.00691 0.00172 -0.0052 0.2836 0.8776 1.500 0.2636 0.00701 0.00177 -0.0054 0.2730 0.8844 1.750 0.2933 0.00713 0.00181 -0.0058 0.2625 0.8888 2.000 0.3223 0.00722 0.00186 -0.0060 0.2515 0.8919 2.250 0.3513 0.00732 0.00192 -0.0062 0.2431 0.8952 2.500 0.3805 0.00744 0.00198 -0.0065 0.2326 0.8987 2.750 0.4099 0.00755 0.00205 -0.0068 0.2232 0.9020 3.000 0.4392 0.00767 0.00212 -0.0072 0.2154 0.9050 3.250 0.4678 0.00778 0.00220 -0.0073 0.2059 0.9077 3.500 0.4966 0.00790 0.00230 -0.0075 0.1972 0.9105 3.750 0.5255 0.00805 0.00239 -0.0078 0.1888 0.9134 4.000 0.5546 0.00817 0.00250 -0.0081 0.1807 0.9162 4.250 0.5837 0.00834 0.00261 -0.0084 0.1719 0.9187 4.500 0.6123 0.00846 0.00273 -0.0086 0.1647 0.9210 4.750 0.6406 0.00862 0.00285 -0.0088 0.1567 0.9233 5.000 0.6690 0.00878 0.00299 -0.0090 0.1482 0.9257 5.250 0.6975 0.00896 0.00314 -0.0092 0.1395 0.9281 5.500 0.7260 0.00918 0.00331 -0.0095 0.1278 0.9305 5.750 0.7546 0.00942 0.00349 -0.0098 0.1175 0.9327 6.000 0.7827 0.00961 0.00367 -0.0100 0.1099 0.9349 6.250 0.8104 0.00982 0.00386 -0.0101 0.1020 0.9371 6.500 0.8381 0.01006 0.00406 -0.0102 0.0940 0.9394 6.750 0.8659 0.01028 0.00428 -0.0104 0.0868 0.9418 7.000 0.8937 0.01057 0.00453 -0.0106 0.0786 0.9442 7.250 0.9214 0.01086 0.00479 -0.0108 0.0706 0.9464 7.500 0.9486 0.01114 0.00506 -0.0108 0.0630 0.9488 7.750 0.9750 0.01148 0.00537 -0.0108 0.0541 0.9516 8.000 1.0015 0.01185 0.00570 -0.0108 0.0463 0.9544 8.250 1.0280 0.01223 0.00606 -0.0108 0.0399 0.9575 8.750 1.0803 0.01294 0.00679 -0.0108 0.0316 0.9642 9.000 1.1059 0.01334 0.00718 -0.0106 0.0282 0.9688 9.500 1.1588 0.01407 0.00798 -0.0108 0.0242 0.9844 9.750 1.1858 0.01454 0.00846 -0.0110 0.0223 1.0000 10.000 1.2126 0.01494 0.00891 -0.0113 0.0213 1.0000 10.250 1.2390 0.01539 0.00939 -0.0114 0.0203 1.0000 10.500 1.2648 0.01589 0.00992 -0.0116 0.0191 1.0000 10.750 1.2900 0.01647 0.01053 -0.0116 0.0178 1.0000 11.000 1.3155 0.01693 0.01105 -0.0117 0.0173 1.0000 11.250 1.3405 0.01743 0.01161 -0.0117 0.0167 1.0000 11.500 1.3650 0.01798 0.01221 -0.0116 0.0161 1.0000 11.750 1.3889 0.01858 0.01285 -0.0115 0.0154 1.0000 12.000 1.4119 0.01924 0.01357 -0.0113 0.0148 1.0000 12.250 1.4339 0.02001 0.01439 -0.0110 0.0141 1.0000 12.500 1.4566 0.02061 0.01506 -0.0108 0.0138 1.0000 12.750 1.4783 0.02127 0.01581 -0.0104 0.0134 1.0000 13.000 1.4992 0.02198 0.01659 -0.0100 0.0131 1.0000 13.250 1.5191 0.02275 0.01744 -0.0095 0.0127 1.0000 13.500 1.5379 0.02357 0.01833 -0.0089 0.0123 1.0000 13.750 1.5552 0.02447 0.01929 -0.0081 0.0120 1.0000 14.000 1.5704 0.02548 0.02038 -0.0072 0.0116 1.0000 14.250 1.5820 0.02669 0.02168 -0.0060 0.0113 1.0000 14.500 1.5900 0.02786 0.02294 -0.0042 0.0110 1.0000 14.750 1.5974 0.02906 0.02425 -0.0027 0.0109 1.0000 15.000 1.6036 0.03048 0.02577 -0.0013 0.0107 1.0000 15.250 1.6084 0.03212 0.02752 -0.0001 0.0105 1.0000 15.500 1.6114 0.03405 0.02956 0.0008 0.0104 1.0000 15.750 1.6126 0.03632 0.03195 0.0013 0.0102 1.0000 16.000 1.6114 0.03906 0.03481 0.0013 0.0101 1.0000 16.250 1.6076 0.04239 0.03827 0.0006 0.0100 1.0000 16.500 1.5999 0.04661 0.04264 -0.0010 0.0098 1.0000 16.750 1.5870 0.05212 0.04830 -0.0038 0.0098 1.0000 17.000 1.5657 0.05975 0.05612 -0.0084 0.0097 1.0000 17.250 1.5324 0.07028 0.06687 -0.0148 0.0098 1.0000 17.500 1.4843 0.08296 0.07977 -0.0216 0.0099 1.0000 17.750 1.4304 0.09605 0.09304 -0.0282 0.0101 1.0000