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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.7077 0.07805 0.07654 0.0038 0.9244 0.0045 -8.750 -0.7255 0.07046 0.06884 -0.0022 0.9176 0.0045 -8.500 -0.7336 0.06335 0.06158 -0.0056 0.9119 0.0045 -8.250 -0.7369 0.05674 0.05477 -0.0071 0.9072 0.0047 -7.750 -0.7681 0.02671 0.02313 -0.0048 0.8960 0.0058 -7.500 -0.7492 0.02385 0.01988 -0.0040 0.8929 0.0059 -7.250 -0.7313 0.02002 0.01551 -0.0031 0.8894 0.0061 -7.000 -0.7077 0.01838 0.01364 -0.0028 0.8858 0.0063 -6.750 -0.6833 0.01692 0.01194 -0.0024 0.8823 0.0063 -6.500 -0.6584 0.01569 0.01051 -0.0020 0.8791 0.0063 -6.250 -0.6326 0.01467 0.00933 -0.0018 0.8762 0.0063 -6.000 -0.6062 0.01379 0.00833 -0.0017 0.8729 0.0064 -5.750 -0.5796 0.01303 0.00747 -0.0015 0.8694 0.0064 -5.500 -0.5529 0.01239 0.00673 -0.0014 0.8662 0.0065 -5.250 -0.5260 0.01183 0.00609 -0.0013 0.8633 0.0066 -5.000 -0.4984 0.01132 0.00553 -0.0013 0.8601 0.0067 -4.750 -0.4707 0.01087 0.00503 -0.0014 0.8566 0.0069 -4.500 -0.4429 0.01047 0.00458 -0.0014 0.8532 0.0071 -4.250 -0.4151 0.01011 0.00416 -0.0014 0.8499 0.0073 -4.000 -0.3869 0.00978 0.00379 -0.0015 0.8465 0.0076 -3.750 -0.3584 0.00948 0.00345 -0.0017 0.8426 0.0080 -3.500 -0.3300 0.00923 0.00316 -0.0018 0.8388 0.0084 -3.250 -0.3016 0.00895 0.00284 -0.0019 0.8353 0.0090 -3.000 -0.2730 0.00872 0.00261 -0.0021 0.8319 0.0099 -2.750 -0.2440 0.00853 0.00242 -0.0024 0.8281 0.0109 -2.500 -0.2152 0.00837 0.00223 -0.0026 0.8238 0.0119 -2.250 -0.1865 0.00819 0.00204 -0.0027 0.8172 0.0140 -2.000 -0.1578 0.00806 0.00188 -0.0029 0.8060 0.0163 -1.750 -0.1291 0.00792 0.00171 -0.0030 0.7882 0.0215 -1.500 -0.1001 0.00776 0.00155 -0.0032 0.7665 0.0343 -1.250 -0.0711 0.00752 0.00141 -0.0036 0.7495 0.0769 -1.000 -0.0420 0.00719 0.00128 -0.0040 0.7349 0.1522 -0.750 -0.0130 0.00660 0.00112 -0.0047 0.7162 0.3064 -0.500 0.0160 0.00575 0.00096 -0.0057 0.6773 0.5494 -0.250 0.0452 0.00536 0.00095 -0.0064 0.6242 0.7146 0.000 0.0744 0.00541 0.00101 -0.0068 0.5714 0.7792 0.250 0.1037 0.00559 0.00106 -0.0072 0.5123 0.8079 0.500 0.1333 0.00586 0.00110 -0.0078 0.4469 0.8192 0.750 0.1628 0.00617 0.00117 -0.0084 0.3775 0.8287 1.000 0.1920 0.00643 0.00124 -0.0088 0.3232 0.8380 1.250 0.2209 0.00661 0.00130 -0.0092 0.2884 0.8467 1.500 0.2499 0.00678 0.00136 -0.0095 0.2619 0.8559 1.750 0.2784 0.00690 0.00143 -0.0097 0.2408 0.8648 2.000 0.3069 0.00703 0.00150 -0.0099 0.2227 0.8741 2.250 0.3352 0.00716 0.00159 -0.0101 0.2073 0.8836 2.500 0.3632 0.00729 0.00167 -0.0102 0.1933 0.8927 2.750 0.3914 0.00742 0.00177 -0.0103 0.1808 0.9018 3.000 0.4190 0.00754 0.00186 -0.0103 0.1717 0.9107 3.250 0.4467 0.00767 0.00198 -0.0103 0.1637 0.9189 3.500 0.4742 0.00778 0.00208 -0.0102 0.1580 0.9271 3.750 0.5015 0.00790 0.00219 -0.0102 0.1525 0.9342 4.000 0.5288 0.00804 0.00232 -0.0101 0.1457 0.9416 4.250 0.5558 0.00817 0.00244 -0.0100 0.1382 0.9480 4.500 0.5826 0.00832 0.00256 -0.0098 0.1323 0.9549 4.750 0.6096 0.00843 0.00268 -0.0097 0.1285 0.9610 5.000 0.6362 0.00857 0.00282 -0.0095 0.1227 0.9677 5.250 0.6634 0.00871 0.00295 -0.0095 0.1183 0.9741 5.500 0.6916 0.00883 0.00309 -0.0096 0.1131 0.9810 5.750 0.7214 0.00903 0.00326 -0.0103 0.1058 0.9877 6.250 0.7807 0.00945 0.00363 -0.0115 0.0883 1.0000 6.500 0.8084 0.00984 0.00390 -0.0119 0.0690 1.0000 6.750 0.8358 0.01024 0.00423 -0.0122 0.0543 1.0000 7.000 0.8634 0.01060 0.00455 -0.0124 0.0459 1.0000 7.250 0.8909 0.01093 0.00487 -0.0127 0.0399 1.0000 7.500 0.9182 0.01128 0.00520 -0.0129 0.0347 1.0000 7.750 0.9453 0.01166 0.00557 -0.0131 0.0294 1.0000 8.000 0.9723 0.01201 0.00593 -0.0133 0.0258 1.0000 8.250 0.9989 0.01244 0.00634 -0.0134 0.0217 1.0000 8.500 1.0256 0.01281 0.00673 -0.0135 0.0192 1.0000 8.750 1.0518 0.01326 0.00719 -0.0136 0.0166 1.0000 9.000 1.0781 0.01367 0.00763 -0.0137 0.0151 1.0000 9.250 1.1041 0.01409 0.00808 -0.0137 0.0140 1.0000 9.500 1.1297 0.01456 0.00859 -0.0137 0.0129 1.0000 9.750 1.1548 0.01510 0.00916 -0.0136 0.0118 1.0000 10.000 1.1798 0.01563 0.00975 -0.0135 0.0112 1.0000 10.250 1.2048 0.01610 0.01029 -0.0135 0.0108 1.0000 10.500 1.2295 0.01659 0.01083 -0.0134 0.0102 1.0000 10.750 1.2537 0.01712 0.01140 -0.0132 0.0095 1.0000 11.000 1.2772 0.01773 0.01205 -0.0130 0.0089 1.0000 11.250 1.2998 0.01844 0.01284 -0.0127 0.0083 1.0000 11.500 1.3222 0.01912 0.01360 -0.0123 0.0080 1.0000 11.750 1.3448 0.01972 0.01427 -0.0120 0.0078 1.0000 12.000 1.3667 0.02038 0.01501 -0.0116 0.0076 1.0000 12.250 1.3878 0.02107 0.01579 -0.0111 0.0073 1.0000 12.500 1.4083 0.02180 0.01659 -0.0106 0.0070 1.0000 12.750 1.4279 0.02257 0.01744 -0.0100 0.0068 1.0000 13.000 1.4464 0.02339 0.01834 -0.0093 0.0065 1.0000 13.250 1.4635 0.02429 0.01933 -0.0085 0.0062 1.0000 13.500 1.4784 0.02534 0.02047 -0.0074 0.0059 1.0000 13.750 1.4897 0.02659 0.02182 -0.0060 0.0056 1.0000 14.000 1.5003 0.02755 0.02289 -0.0044 0.0055 1.0000 14.250 1.5097 0.02865 0.02409 -0.0029 0.0054 1.0000 14.500 1.5180 0.02988 0.02542 -0.0014 0.0052 1.0000 14.750 1.5251 0.03126 0.02691 -0.0001 0.0050 1.0000 15.000 1.5309 0.03282 0.02858 0.0011 0.0048 1.0000 15.250 1.5353 0.03458 0.03044 0.0021 0.0046 1.0000 15.500 1.5379 0.03660 0.03257 0.0029 0.0043 1.0000 15.750 1.5378 0.03900 0.03508 0.0034 0.0042 1.0000 16.000 1.5349 0.04188 0.03807 0.0036 0.0040 1.0000 16.250 1.5282 0.04544 0.04177 0.0031 0.0039 1.0000 16.500 1.5170 0.04999 0.04647 0.0017 0.0037 1.0000 16.750 1.5004 0.05595 0.05259 -0.0011 0.0037 1.0000 17.250 1.4285 0.07845 0.07559 -0.0152 0.0039 1.0000 17.500 1.3372 0.10058 0.09804 -0.0270 0.0045 1.0000 17.750 1.2587 0.11948 0.11713 -0.0368 0.0050 1.0000