XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094 R8 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5095 0.09735 0.09374 0.0029 1.0000 0.0355 -8.500 -0.5156 0.09129 0.08772 -0.0033 1.0000 0.0363 -8.250 -0.5199 0.08542 0.08189 -0.0095 1.0000 0.0364 -7.750 -0.5208 0.07365 0.07002 -0.0209 1.0000 0.0364 -7.250 -0.5158 0.06059 0.05673 -0.0255 1.0000 0.0255 -7.000 -0.5057 0.05685 0.05290 -0.0267 1.0000 0.0251 -6.750 -0.4955 0.05234 0.04823 -0.0278 1.0000 0.0246 -6.500 -0.4847 0.04736 0.04302 -0.0285 1.0000 0.0242 -6.250 -0.4733 0.04216 0.03749 -0.0285 1.0000 0.0238 -6.000 -0.4612 0.03723 0.03218 -0.0277 1.0000 0.0236 -5.750 -0.4465 0.03413 0.02881 -0.0265 1.0000 0.0241 -5.500 -0.4319 0.03072 0.02501 -0.0250 1.0000 0.0247 -5.250 -0.4161 0.02757 0.02144 -0.0234 1.0000 0.0249 -5.000 -0.3987 0.02499 0.01846 -0.0217 1.0000 0.0249 -4.750 -0.3675 0.02248 0.01549 -0.0226 0.9960 0.0251 -4.500 -0.3326 0.02047 0.01305 -0.0240 0.9916 0.0255 -4.250 -0.2965 0.01902 0.01137 -0.0257 0.9876 0.0260 -4.000 -0.2610 0.01807 0.01037 -0.0272 0.9818 0.0266 -3.750 -0.2209 0.01710 0.00931 -0.0296 0.9744 0.0274 -3.500 -0.1845 0.01624 0.00830 -0.0310 0.9616 0.0288 -3.250 -0.1521 0.01562 0.00769 -0.0317 0.9486 0.0302 -3.000 -0.1210 0.01501 0.00707 -0.0321 0.9381 0.0316 -2.750 -0.0932 0.01441 0.00642 -0.0317 0.9251 0.0328 -2.500 -0.0655 0.01391 0.00597 -0.0314 0.9124 0.0340 -2.250 -0.0381 0.01347 0.00551 -0.0309 0.8988 0.0359 -2.000 -0.0116 0.01311 0.00517 -0.0302 0.8837 0.0385 -1.750 0.0144 0.01276 0.00480 -0.0294 0.8662 0.0414 -1.500 0.0397 0.01245 0.00443 -0.0283 0.8430 0.0446 -1.250 0.0646 0.01219 0.00412 -0.0271 0.8110 0.0496 -1.000 0.0898 0.01196 0.00382 -0.0260 0.7761 0.0571 -0.750 0.1155 0.01175 0.00355 -0.0251 0.7417 0.0722 -0.500 0.1412 0.01150 0.00333 -0.0243 0.7013 0.1145 -0.250 0.1654 0.01076 0.00311 -0.0238 0.6550 0.3084 0.000 0.1783 0.00932 0.00320 -0.0203 0.6095 0.7779 0.250 0.1958 0.00937 0.00329 -0.0166 0.5589 0.9015 0.500 0.2301 0.00965 0.00329 -0.0170 0.4987 0.9693 0.750 0.2880 0.01005 0.00325 -0.0231 0.4306 1.0000 1.000 0.3119 0.01031 0.00324 -0.0224 0.3916 1.0000 1.250 0.3360 0.01055 0.00325 -0.0217 0.3584 1.0000 1.500 0.3602 0.01080 0.00328 -0.0210 0.3294 1.0000 1.750 0.3849 0.01104 0.00333 -0.0204 0.3029 1.0000 2.000 0.4100 0.01130 0.00341 -0.0199 0.2778 1.0000 2.250 0.4355 0.01156 0.00350 -0.0195 0.2540 1.0000 2.500 0.4613 0.01183 0.00361 -0.0191 0.2313 1.0000 2.750 0.4872 0.01212 0.00375 -0.0187 0.2114 1.0000 3.000 0.5133 0.01242 0.00391 -0.0184 0.1954 1.0000 3.250 0.5396 0.01272 0.00409 -0.0182 0.1828 1.0000 3.500 0.5659 0.01304 0.00429 -0.0179 0.1721 1.0000 3.750 0.5924 0.01333 0.00452 -0.0177 0.1630 1.0000 4.000 0.6188 0.01366 0.00476 -0.0174 0.1556 1.0000 4.250 0.6454 0.01397 0.00502 -0.0172 0.1489 1.0000 4.500 0.6716 0.01433 0.00530 -0.0169 0.1434 1.0000 4.750 0.6982 0.01463 0.00560 -0.0167 0.1379 1.0000 5.000 0.7244 0.01501 0.00591 -0.0165 0.1332 1.0000 5.250 0.7506 0.01536 0.00624 -0.0162 0.1292 1.0000 5.500 0.7769 0.01572 0.00660 -0.0160 0.1254 1.0000 5.750 0.8028 0.01612 0.00696 -0.0157 0.1221 1.0000 6.000 0.8284 0.01656 0.00737 -0.0154 0.1191 1.0000 6.250 0.8545 0.01694 0.00777 -0.0152 0.1161 1.0000 6.500 0.8802 0.01735 0.00820 -0.0149 0.1133 1.0000 6.750 0.9055 0.01782 0.00863 -0.0146 0.1109 1.0000 7.000 0.9304 0.01835 0.00914 -0.0142 0.1089 1.0000 7.250 0.9558 0.01882 0.00968 -0.0139 0.1070 1.0000 7.500 0.9809 0.01931 0.01020 -0.0136 0.1050 1.0000 7.750 1.0058 0.01980 0.01072 -0.0132 0.1030 1.0000 8.000 1.0303 0.02033 0.01126 -0.0129 0.1013 1.0000 8.250 1.0541 0.02099 0.01188 -0.0125 0.0998 1.0000 8.500 1.0786 0.02155 0.01253 -0.0121 0.0983 1.0000 8.750 1.1027 0.02216 0.01324 -0.0117 0.0969 1.0000 9.000 1.1264 0.02279 0.01394 -0.0112 0.0955 1.0000 9.250 1.1499 0.02344 0.01464 -0.0108 0.0942 1.0000 9.500 1.1731 0.02409 0.01535 -0.0103 0.0930 1.0000 9.750 1.1959 0.02477 0.01605 -0.0098 0.0919 1.0000 10.000 1.2182 0.02557 0.01684 -0.0093 0.0908 1.0000 10.250 1.2403 0.02636 0.01778 -0.0088 0.0897 1.0000 10.500 1.2619 0.02719 0.01876 -0.0081 0.0887 1.0000 10.750 1.2829 0.02806 0.01977 -0.0075 0.0877 1.0000 11.000 1.3034 0.02896 0.02079 -0.0068 0.0867 1.0000 11.250 1.3235 0.02986 0.02180 -0.0061 0.0858 1.0000 11.500 1.3430 0.03075 0.02278 -0.0054 0.0848 1.0000 11.750 1.3622 0.03162 0.02373 -0.0047 0.0840 1.0000 12.000 1.3810 0.03255 0.02470 -0.0039 0.0832 1.0000 12.250 1.3995 0.03365 0.02583 -0.0032 0.0824 1.0000 12.500 1.4135 0.03494 0.02737 -0.0020 0.0817 1.0000 12.750 1.4257 0.03634 0.02900 -0.0007 0.0810 1.0000 13.000 1.4360 0.03780 0.03068 0.0007 0.0802 1.0000 13.250 1.4435 0.03926 0.03235 0.0024 0.0793 1.0000 13.500 1.4481 0.04073 0.03399 0.0043 0.0785 1.0000 13.750 1.4522 0.04229 0.03571 0.0060 0.0778 1.0000 14.000 1.4561 0.04392 0.03747 0.0073 0.0771 1.0000 14.250 1.4612 0.04546 0.03911 0.0084 0.0764 1.0000 14.500 1.4692 0.04679 0.04048 0.0092 0.0756 1.0000 14.750 1.4790 0.04813 0.04181 0.0098 0.0748 1.0000 15.000 1.4631 0.05182 0.04583 0.0100 0.0741 1.0000 15.250 1.4459 0.05622 0.05053 0.0090 0.0733 1.0000 15.500 1.4265 0.06147 0.05606 0.0069 0.0726 1.0000 15.750 1.4018 0.06809 0.06295 0.0034 0.0721 1.0000 16.000 1.3623 0.07786 0.07301 -0.0029 0.0717 1.0000