XFOIL Version 6.96 Calculated polar for: ONERA OA213 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5017 0.08379 0.08063 -0.0007 0.8335 0.0192 -8.000 -0.5019 0.07998 0.07680 -0.0035 0.8287 0.0189 -7.750 -0.5036 0.07574 0.07250 -0.0058 0.8247 0.0186 -7.250 -0.5190 0.05651 0.05267 -0.0137 0.8168 0.0158 -7.000 -0.5097 0.05214 0.04810 -0.0143 0.8124 0.0157 -6.750 -0.5002 0.04739 0.04305 -0.0141 0.8087 0.0155 -6.500 -0.4906 0.04201 0.03725 -0.0133 0.8057 0.0154 -6.250 -0.4767 0.03587 0.03051 -0.0129 0.8011 0.0154 -6.000 -0.4597 0.03066 0.02456 -0.0119 0.7967 0.0156 -5.750 -0.4389 0.02741 0.02072 -0.0108 0.7928 0.0159 -5.500 -0.4159 0.02597 0.01906 -0.0101 0.7896 0.0163 -5.250 -0.3886 0.02491 0.01786 -0.0103 0.7844 0.0170 -5.000 -0.3620 0.02363 0.01632 -0.0101 0.7796 0.0182 -4.750 -0.3360 0.02199 0.01424 -0.0093 0.7756 0.0192 -4.500 -0.3104 0.02077 0.01288 -0.0087 0.7720 0.0197 -4.250 -0.2816 0.01986 0.01190 -0.0090 0.7661 0.0205 -4.000 -0.2545 0.01898 0.01091 -0.0087 0.7613 0.0214 -3.750 -0.2285 0.01812 0.00990 -0.0080 0.7574 0.0225 -3.500 -0.2000 0.01739 0.00914 -0.0081 0.7515 0.0241 -3.250 -0.1724 0.01690 0.00863 -0.0080 0.7459 0.0263 -3.000 -0.1461 0.01628 0.00791 -0.0074 0.7415 0.0284 -2.750 -0.1176 0.01575 0.00740 -0.0076 0.7351 0.0308 -2.500 -0.0899 0.01526 0.00688 -0.0074 0.7290 0.0344 -2.250 -0.0630 0.01486 0.00642 -0.0070 0.7234 0.0395 -2.000 -0.0345 0.01442 0.00599 -0.0071 0.7133 0.0462 -1.750 -0.0069 0.01401 0.00555 -0.0068 0.7024 0.0571 -1.500 0.0200 0.01358 0.00514 -0.0064 0.6921 0.0751 -1.250 0.0486 0.01319 0.00486 -0.0066 0.6811 0.1090 -1.000 0.0759 0.01261 0.00459 -0.0067 0.6714 0.1950 -0.750 0.0898 0.01041 0.00445 -0.0043 0.6625 0.7233 -0.500 0.1099 0.01030 0.00462 -0.0014 0.6521 0.8490 -0.250 0.1326 0.01033 0.00461 0.0007 0.6419 0.8945 0.000 0.1579 0.01036 0.00455 0.0021 0.6304 0.9236 0.250 0.1895 0.01042 0.00451 0.0021 0.6177 0.9465 0.500 0.2308 0.01054 0.00450 0.0000 0.6030 0.9693 0.750 0.2734 0.01062 0.00441 -0.0028 0.5872 0.9768 1.000 0.3070 0.01066 0.00430 -0.0041 0.5707 0.9801 1.250 0.3398 0.01072 0.00421 -0.0052 0.5532 0.9835 1.500 0.3751 0.01081 0.00413 -0.0069 0.5336 0.9856 1.750 0.4101 0.01092 0.00410 -0.0086 0.5116 0.9883 2.000 0.4442 0.01107 0.00408 -0.0102 0.4874 0.9914 2.250 0.4779 0.01126 0.00410 -0.0117 0.4599 0.9944 2.500 0.5124 0.01150 0.00415 -0.0135 0.4300 0.9971 2.750 0.5460 0.01179 0.00424 -0.0152 0.3998 1.0000 3.000 0.5715 0.01209 0.00435 -0.0153 0.3730 1.0000 3.250 0.5965 0.01239 0.00450 -0.0153 0.3492 1.0000 3.500 0.6211 0.01272 0.00468 -0.0152 0.3294 1.0000 3.750 0.6455 0.01302 0.00486 -0.0151 0.3133 1.0000 4.000 0.6698 0.01333 0.00507 -0.0149 0.2992 1.0000 4.250 0.6942 0.01365 0.00530 -0.0147 0.2864 1.0000 4.500 0.7189 0.01398 0.00555 -0.0146 0.2749 1.0000 4.750 0.7438 0.01434 0.00581 -0.0146 0.2644 1.0000 5.000 0.7693 0.01465 0.00609 -0.0146 0.2554 1.0000 5.250 0.7946 0.01504 0.00640 -0.0147 0.2475 1.0000 5.500 0.8204 0.01535 0.00669 -0.0147 0.2399 1.0000 5.750 0.8457 0.01576 0.00703 -0.0148 0.2327 1.0000 6.000 0.8714 0.01609 0.00738 -0.0149 0.2259 1.0000 6.250 0.8966 0.01649 0.00774 -0.0150 0.2196 1.0000 6.500 0.9216 0.01690 0.00813 -0.0151 0.2145 1.0000 6.750 0.9469 0.01727 0.00853 -0.0151 0.2093 1.0000 7.000 0.9714 0.01772 0.00895 -0.0151 0.2046 1.0000 7.250 0.9954 0.01819 0.00941 -0.0151 0.2006 1.0000 7.500 1.0201 0.01859 0.00987 -0.0151 0.1963 1.0000 7.750 1.0440 0.01905 0.01034 -0.0150 0.1920 1.0000 8.000 1.0668 0.01958 0.01085 -0.0149 0.1881 1.0000 8.250 1.0900 0.02008 0.01139 -0.0148 0.1847 1.0000 8.500 1.1133 0.02055 0.01193 -0.0147 0.1813 1.0000 8.750 1.1357 0.02107 0.01250 -0.0145 0.1781 1.0000 9.000 1.1571 0.02166 0.01311 -0.0143 0.1753 1.0000 9.250 1.1775 0.02234 0.01378 -0.0140 0.1728 1.0000 9.500 1.1989 0.02292 0.01445 -0.0137 0.1705 1.0000 9.750 1.2198 0.02352 0.01514 -0.0134 0.1681 1.0000 10.000 1.2391 0.02414 0.01585 -0.0130 0.1653 1.0000 10.250 1.2559 0.02481 0.01657 -0.0123 0.1622 1.0000 10.500 1.2712 0.02562 0.01736 -0.0115 0.1589 1.0000 10.750 1.2883 0.02632 0.01818 -0.0109 0.1553 1.0000 11.000 1.3049 0.02705 0.01902 -0.0104 0.1515 1.0000 11.250 1.3203 0.02788 0.01992 -0.0098 0.1483 1.0000 11.500 1.3342 0.02885 0.02091 -0.0092 0.1456 1.0000 11.750 1.3494 0.02976 0.02193 -0.0087 0.1429 1.0000 12.000 1.3647 0.03067 0.02299 -0.0083 0.1394 1.0000 12.250 1.3782 0.03170 0.02412 -0.0078 0.1361 1.0000 12.500 1.3899 0.03289 0.02537 -0.0073 0.1332 1.0000 12.750 1.4016 0.03413 0.02668 -0.0069 0.1306 1.0000 13.000 1.4150 0.03525 0.02799 -0.0065 0.1275 1.0000 13.250 1.4256 0.03661 0.02947 -0.0062 0.1231 1.0000 13.500 1.4323 0.03834 0.03123 -0.0060 0.1192 1.0000 13.750 1.4437 0.03973 0.03280 -0.0058 0.1144 1.0000 14.000 1.4502 0.04159 0.03476 -0.0057 0.1089 1.0000 14.250 1.4571 0.04349 0.03677 -0.0056 0.1029 1.0000 14.500 1.4595 0.04589 0.03925 -0.0057 0.0941 1.0000 14.750 1.4569 0.04892 0.04230 -0.0060 0.0783 1.0000 15.000 1.4352 0.05439 0.04761 -0.0070 0.0501 1.0000 15.250 1.4123 0.06038 0.05359 -0.0084 0.0401 1.0000 15.500 1.3933 0.06623 0.05954 -0.0100 0.0358 1.0000 15.750 1.3763 0.07210 0.06555 -0.0120 0.0338 1.0000 16.000 1.3581 0.07843 0.07204 -0.0143 0.0324 1.0000 16.250 1.3377 0.08534 0.07913 -0.0171 0.0316 1.0000 16.500 1.3152 0.09289 0.08687 -0.0202 0.0311 1.0000 16.750 1.2903 0.10108 0.09526 -0.0238 0.0310 1.0000 17.000 1.2634 0.10986 0.10424 -0.0277 0.0311 1.0000 17.250 1.2354 0.11906 0.11363 -0.0320 0.0314 1.0000