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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.6392 0.08547 0.08341 0.0095 1.0000 0.0093 -8.500 -0.6468 0.07788 0.07581 0.0002 1.0000 0.0092 -8.250 -0.6512 0.07111 0.06894 -0.0058 0.9797 0.0092 -8.000 -0.6535 0.06481 0.06249 -0.0091 0.9716 0.0093 -7.750 -0.6543 0.05861 0.05609 -0.0106 0.9648 0.0094 -7.500 -0.6507 0.05224 0.04947 -0.0115 0.9594 0.0096 -7.000 -0.6628 0.02393 0.01901 -0.0081 0.9486 0.0100 -6.750 -0.6407 0.02180 0.01659 -0.0076 0.9451 0.0103 -6.500 -0.6167 0.02089 0.01555 -0.0072 0.9418 0.0105 -6.250 -0.5934 0.01981 0.01429 -0.0064 0.9388 0.0107 -6.000 -0.5671 0.01862 0.01291 -0.0063 0.9356 0.0110 -5.750 -0.5411 0.01748 0.01158 -0.0060 0.9320 0.0114 -5.500 -0.5157 0.01656 0.01050 -0.0055 0.9286 0.0120 -5.250 -0.4907 0.01573 0.00948 -0.0048 0.9254 0.0126 -5.000 -0.4638 0.01484 0.00846 -0.0046 0.9218 0.0130 -4.750 -0.4377 0.01418 0.00775 -0.0043 0.9166 0.0134 -4.500 -0.4135 0.01369 0.00722 -0.0034 0.9110 0.0138 -4.250 -0.3865 0.01318 0.00666 -0.0031 0.9040 0.0144 -4.000 -0.3606 0.01268 0.00610 -0.0026 0.8977 0.0150 -3.750 -0.3338 0.01219 0.00555 -0.0023 0.8915 0.0156 -3.500 -0.3065 0.01173 0.00504 -0.0021 0.8842 0.0163 -3.250 -0.2798 0.01138 0.00469 -0.0018 0.8774 0.0174 -3.000 -0.2519 0.01106 0.00436 -0.0017 0.8686 0.0186 -2.750 -0.2244 0.01073 0.00398 -0.0015 0.8596 0.0196 -2.500 -0.1972 0.01037 0.00359 -0.0012 0.8492 0.0208 -2.250 -0.1695 0.01011 0.00331 -0.0010 0.8358 0.0224 -2.000 -0.1419 0.00991 0.00304 -0.0008 0.8195 0.0245 -1.750 -0.1142 0.00969 0.00278 -0.0006 0.8023 0.0275 -1.500 -0.0858 0.00953 0.00256 -0.0006 0.7843 0.0308 -1.250 -0.0573 0.00938 0.00237 -0.0006 0.7631 0.0363 -1.000 -0.0286 0.00927 0.00219 -0.0007 0.7377 0.0456 -0.750 0.0004 0.00916 0.00205 -0.0009 0.7071 0.0648 -0.500 0.0298 0.00897 0.00191 -0.0013 0.6685 0.1231 -0.250 0.0595 0.00701 0.00168 -0.0033 0.6181 0.6744 0.000 0.0859 0.00690 0.00179 -0.0028 0.5564 0.7985 0.250 0.1121 0.00721 0.00192 -0.0022 0.4823 0.8470 0.500 0.1386 0.00756 0.00205 -0.0018 0.4205 0.8759 0.750 0.1640 0.00784 0.00218 -0.0010 0.3836 0.8964 1.000 0.1911 0.00804 0.00225 -0.0007 0.3593 0.9073 1.250 0.2194 0.00817 0.00228 -0.0008 0.3407 0.9113 1.500 0.2483 0.00831 0.00232 -0.0010 0.3246 0.9156 1.750 0.2776 0.00844 0.00236 -0.0014 0.3109 0.9195 2.000 0.3053 0.00854 0.00240 -0.0013 0.2978 0.9230 2.250 0.3334 0.00864 0.00245 -0.0013 0.2862 0.9268 2.500 0.3620 0.00876 0.00250 -0.0015 0.2752 0.9308 2.750 0.3906 0.00889 0.00257 -0.0017 0.2637 0.9343 3.000 0.4180 0.00897 0.00263 -0.0015 0.2537 0.9377 3.250 0.4459 0.00909 0.00270 -0.0015 0.2436 0.9414 3.750 0.5023 0.00934 0.00288 -0.0018 0.2245 0.9484 4.000 0.5294 0.00946 0.00296 -0.0016 0.2150 0.9520 4.250 0.5571 0.00960 0.00307 -0.0017 0.2053 0.9557 4.500 0.5852 0.00973 0.00320 -0.0018 0.1974 0.9595 4.750 0.6127 0.00989 0.00332 -0.0018 0.1878 0.9631 5.000 0.6404 0.01003 0.00345 -0.0018 0.1792 0.9672 5.250 0.6686 0.01020 0.00361 -0.0020 0.1712 0.9715 5.500 0.6975 0.01039 0.00378 -0.0024 0.1619 0.9760 5.750 0.7271 0.01059 0.00397 -0.0029 0.1532 0.9811 6.000 0.7572 0.01084 0.00417 -0.0037 0.1419 0.9875 6.250 0.7871 0.01112 0.00441 -0.0044 0.1309 1.0000 6.500 0.8160 0.01138 0.00466 -0.0049 0.1218 1.0000 6.750 0.8448 0.01168 0.00494 -0.0054 0.1132 1.0000 7.000 0.8733 0.01202 0.00525 -0.0058 0.1041 1.0000 7.250 0.9018 0.01233 0.00556 -0.0063 0.0959 1.0000 7.500 0.9300 0.01268 0.00590 -0.0067 0.0878 1.0000 7.750 0.9578 0.01308 0.00627 -0.0071 0.0787 1.0000 8.000 0.9854 0.01350 0.00667 -0.0074 0.0695 1.0000 8.250 1.0129 0.01393 0.00709 -0.0078 0.0610 1.0000 8.500 1.0399 0.01442 0.00756 -0.0080 0.0526 1.0000 8.750 1.0665 0.01495 0.00808 -0.0083 0.0452 1.0000 9.000 1.0928 0.01551 0.00863 -0.0085 0.0396 1.0000 9.250 1.1190 0.01605 0.00920 -0.0087 0.0355 1.0000 9.500 1.1447 0.01662 0.00980 -0.0088 0.0324 1.0000 9.750 1.1703 0.01719 0.01041 -0.0089 0.0298 1.0000 10.000 1.1948 0.01789 0.01115 -0.0089 0.0273 1.0000 10.250 1.2199 0.01845 0.01179 -0.0089 0.0260 1.0000 10.500 1.2442 0.01908 0.01249 -0.0088 0.0246 1.0000 10.750 1.2676 0.01980 0.01327 -0.0087 0.0233 1.0000 11.000 1.2897 0.02068 0.01422 -0.0085 0.0221 1.0000 11.250 1.3126 0.02136 0.01499 -0.0082 0.0213 1.0000 11.500 1.3345 0.02210 0.01583 -0.0079 0.0204 1.0000 11.750 1.3556 0.02291 0.01673 -0.0076 0.0196 1.0000 12.000 1.3752 0.02382 0.01772 -0.0071 0.0188 1.0000 12.250 1.3925 0.02492 0.01891 -0.0064 0.0182 1.0000 12.500 1.4082 0.02609 0.02018 -0.0056 0.0176 1.0000 12.750 1.4243 0.02711 0.02133 -0.0048 0.0172 1.0000 13.000 1.4383 0.02823 0.02257 -0.0038 0.0168 1.0000 13.250 1.4491 0.02943 0.02389 -0.0026 0.0163 1.0000 13.500 1.4556 0.03078 0.02535 -0.0010 0.0159 1.0000 13.750 1.4614 0.03231 0.02701 0.0003 0.0155 1.0000 14.000 1.4653 0.03413 0.02894 0.0014 0.0152 1.0000 14.250 1.4665 0.03634 0.03127 0.0021 0.0149 1.0000 14.500 1.4647 0.03908 0.03413 0.0023 0.0147 1.0000 14.750 1.4593 0.04255 0.03774 0.0017 0.0145 1.0000 15.000 1.4500 0.04698 0.04233 0.0000 0.0143 1.0000 15.250 1.4368 0.05262 0.04814 -0.0029 0.0142 1.0000 15.500 1.4235 0.05897 0.05467 -0.0068 0.0141 1.0000 15.750 1.4061 0.06648 0.06237 -0.0115 0.0141 1.0000 16.000 1.3846 0.07473 0.07078 -0.0163 0.0141 1.0000 16.250 1.3602 0.08309 0.07929 -0.0207 0.0141 1.0000 16.500 1.3353 0.09132 0.08765 -0.0249 0.0141 1.0000