XFOIL Version 6.96 Calculated polar for: SIKORSKY SSC-A09 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 -0.6471 0.07827 0.07627 -0.0047 0.9642 0.0076 -8.500 -0.6617 0.07203 0.06995 -0.0097 0.9529 0.0075 -8.250 -0.6692 0.06580 0.06358 -0.0127 0.9456 0.0076 -8.000 -0.6726 0.05938 0.05698 -0.0146 0.9392 0.0078 -7.750 -0.6736 0.05279 0.05012 -0.0152 0.9339 0.0080 -7.500 -0.6698 0.04582 0.04281 -0.0153 0.9285 0.0080 -7.250 -0.6640 0.03887 0.03542 -0.0142 0.9237 0.0082 -7.000 -0.6545 0.03225 0.02826 -0.0126 0.9197 0.0083 -6.500 -0.6194 0.02398 0.01894 -0.0106 0.9119 0.0088 -6.250 -0.5976 0.02167 0.01626 -0.0097 0.9087 0.0087 -6.000 -0.5742 0.01979 0.01406 -0.0091 0.9057 0.0087 -5.750 -0.5487 0.01814 0.01216 -0.0088 0.9023 0.0088 -5.500 -0.5232 0.01677 0.01060 -0.0085 0.8990 0.0088 -5.250 -0.4979 0.01569 0.00938 -0.0080 0.8959 0.0090 -5.000 -0.4726 0.01483 0.00841 -0.0076 0.8931 0.0091 -4.750 -0.4459 0.01410 0.00760 -0.0074 0.8901 0.0094 -4.500 -0.4188 0.01344 0.00688 -0.0074 0.8866 0.0097 -4.250 -0.3919 0.01285 0.00622 -0.0072 0.8832 0.0101 -4.000 -0.3654 0.01230 0.00562 -0.0070 0.8802 0.0106 -3.750 -0.3389 0.01182 0.00506 -0.0067 0.8774 0.0112 -3.500 -0.3106 0.01140 0.00459 -0.0068 0.8736 0.0117 -3.250 -0.2829 0.01092 0.00408 -0.0069 0.8698 0.0126 -3.000 -0.2554 0.01060 0.00375 -0.0068 0.8663 0.0138 -2.750 -0.2281 0.01036 0.00347 -0.0067 0.8632 0.0155 -2.500 -0.1993 0.01005 0.00316 -0.0069 0.8592 0.0182 -2.250 -0.1707 0.00983 0.00292 -0.0071 0.8551 0.0212 -2.000 -0.1427 0.00958 0.00267 -0.0071 0.8514 0.0279 -1.750 -0.1149 0.00931 0.00245 -0.0070 0.8464 0.0446 -1.500 -0.0874 0.00880 0.00222 -0.0072 0.8373 0.1258 -1.250 -0.0613 0.00788 0.00192 -0.0073 0.8233 0.3173 -1.000 -0.0359 0.00676 0.00167 -0.0073 0.8059 0.5798 -0.750 -0.0106 0.00619 0.00166 -0.0066 0.7900 0.7427 -0.500 0.0146 0.00600 0.00171 -0.0057 0.7779 0.8173 -0.250 0.0414 0.00595 0.00169 -0.0051 0.7660 0.8447 0.000 0.0695 0.00594 0.00165 -0.0050 0.7528 0.8568 0.250 0.0972 0.00594 0.00160 -0.0048 0.7330 0.8666 0.500 0.1249 0.00599 0.00154 -0.0046 0.7026 0.8759 0.750 0.1528 0.00612 0.00149 -0.0045 0.6563 0.8856 1.000 0.1802 0.00637 0.00149 -0.0044 0.5950 0.8943 1.250 0.2082 0.00673 0.00155 -0.0046 0.5230 0.9033 1.500 0.2356 0.00718 0.00166 -0.0047 0.4383 0.9120 1.750 0.2626 0.00760 0.00178 -0.0048 0.3645 0.9203 2.000 0.2897 0.00792 0.00188 -0.0049 0.3150 0.9291 2.250 0.3162 0.00815 0.00199 -0.0047 0.2813 0.9371 2.500 0.3433 0.00836 0.00208 -0.0046 0.2558 0.9455 2.750 0.3700 0.00854 0.00217 -0.0044 0.2352 0.9534 3.000 0.3973 0.00871 0.00227 -0.0044 0.2184 0.9612 3.250 0.4253 0.00888 0.00238 -0.0046 0.2032 0.9690 3.500 0.4548 0.00905 0.00249 -0.0051 0.1897 0.9757 3.750 0.4856 0.00921 0.00262 -0.0058 0.1798 0.9824 4.000 0.5178 0.00939 0.00276 -0.0070 0.1718 0.9881 4.250 0.5502 0.00957 0.00293 -0.0082 0.1644 0.9952 4.500 0.5799 0.00976 0.00310 -0.0088 0.1570 1.0000 4.750 0.6076 0.00999 0.00328 -0.0091 0.1484 1.0000 5.000 0.6357 0.01018 0.00348 -0.0093 0.1422 1.0000 5.250 0.6637 0.01039 0.00369 -0.0096 0.1367 1.0000 5.500 0.6916 0.01062 0.00391 -0.0098 0.1312 1.0000 5.750 0.7196 0.01082 0.00414 -0.0101 0.1255 1.0000 6.000 0.7473 0.01109 0.00438 -0.0103 0.1188 1.0000 6.250 0.7752 0.01129 0.00462 -0.0106 0.1122 1.0000 6.500 0.8027 0.01157 0.00487 -0.0108 0.1038 1.0000 6.750 0.8300 0.01186 0.00515 -0.0110 0.0929 1.0000 7.000 0.8570 0.01221 0.00545 -0.0112 0.0788 1.0000 7.250 0.8833 0.01269 0.00584 -0.0113 0.0615 1.0000 7.500 0.9094 0.01319 0.00629 -0.0114 0.0502 1.0000 7.750 0.9355 0.01365 0.00677 -0.0114 0.0426 1.0000 8.000 0.9613 0.01416 0.00727 -0.0115 0.0363 1.0000 8.250 0.9873 0.01462 0.00776 -0.0115 0.0317 1.0000 8.500 1.0127 0.01516 0.00831 -0.0115 0.0274 1.0000 8.750 1.0381 0.01566 0.00887 -0.0114 0.0243 1.0000 9.000 1.0626 0.01631 0.00955 -0.0113 0.0213 1.0000 9.250 1.0876 0.01684 0.01015 -0.0112 0.0196 1.0000 9.500 1.1119 0.01743 0.01080 -0.0110 0.0179 1.0000 9.750 1.1353 0.01816 0.01158 -0.0108 0.0163 1.0000 10.000 1.1582 0.01893 0.01245 -0.0105 0.0153 1.0000 10.250 1.1812 0.01962 0.01325 -0.0101 0.0147 1.0000 10.500 1.2034 0.02038 0.01411 -0.0098 0.0140 1.0000 10.750 1.2250 0.02118 0.01502 -0.0093 0.0134 1.0000 11.000 1.2457 0.02203 0.01597 -0.0088 0.0128 1.0000 11.250 1.2652 0.02298 0.01700 -0.0082 0.0122 1.0000 11.500 1.2812 0.02426 0.01841 -0.0073 0.0115 1.0000 11.750 1.2993 0.02521 0.01948 -0.0065 0.0111 1.0000 12.000 1.3173 0.02609 0.02049 -0.0058 0.0106 1.0000 12.250 1.3336 0.02708 0.02160 -0.0049 0.0101 1.0000 12.500 1.3481 0.02815 0.02279 -0.0039 0.0097 1.0000 12.750 1.3598 0.02924 0.02399 -0.0026 0.0093 1.0000 13.000 1.3684 0.03049 0.02535 -0.0010 0.0090 1.0000 13.250 1.3744 0.03200 0.02698 0.0005 0.0086 1.0000 13.500 1.3756 0.03398 0.02909 0.0020 0.0083 1.0000 13.750 1.3739 0.03634 0.03159 0.0033 0.0081 1.0000 14.000 1.3759 0.03852 0.03395 0.0040 0.0080 1.0000 14.250 1.3755 0.04109 0.03669 0.0044 0.0078 1.0000 14.500 1.3723 0.04417 0.03994 0.0043 0.0077 1.0000 14.750 1.3664 0.04787 0.04381 0.0035 0.0075 1.0000 15.000 1.3567 0.05254 0.04866 0.0017 0.0074 1.0000 15.250 1.3427 0.05856 0.05487 -0.0017 0.0074 1.0000 15.500 1.3230 0.06659 0.06311 -0.0069 0.0074 1.0000 15.750 1.2950 0.07707 0.07379 -0.0136 0.0074 1.0000 16.000 1.2620 0.08831 0.08521 -0.0201 0.0075 1.0000 16.250 1.2273 0.09919 0.09622 -0.0257 0.0077 1.0000