XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.4506 0.13201 0.12985 -0.0101 1.0000 0.0186 -12.750 -0.4499 0.12786 0.12571 -0.0121 1.0000 0.0187 -8.000 -0.7083 0.02971 0.02541 -0.0360 0.9931 0.0126 -7.750 -0.6889 0.02543 0.02065 -0.0363 0.9889 0.0120 -7.500 -0.6616 0.02296 0.01782 -0.0372 0.9863 0.0122 -7.250 -0.6316 0.02100 0.01556 -0.0383 0.9844 0.0126 -7.000 -0.6022 0.01886 0.01316 -0.0391 0.9824 0.0124 -6.750 -0.5755 0.01713 0.01121 -0.0393 0.9790 0.0123 -6.500 -0.5456 0.01575 0.00969 -0.0400 0.9764 0.0124 -6.250 -0.5147 0.01463 0.00845 -0.0410 0.9741 0.0126 -6.000 -0.4828 0.01375 0.00747 -0.0422 0.9720 0.0131 -5.750 -0.4551 0.01262 0.00623 -0.0425 0.9689 0.0142 -5.500 -0.4296 0.01204 0.00559 -0.0423 0.9640 0.0163 -5.250 -0.4008 0.01146 0.00494 -0.0426 0.9604 0.0202 -5.000 -0.3731 0.01073 0.00434 -0.0428 0.9571 0.0464 -4.750 -0.3494 0.01035 0.00406 -0.0422 0.9519 0.0710 -4.250 -0.2985 0.00954 0.00352 -0.0417 0.9435 0.1435 -4.000 -0.2767 0.00901 0.00329 -0.0408 0.9381 0.2171 -3.750 -0.2555 0.00835 0.00305 -0.0399 0.9329 0.3226 -3.500 -0.2330 0.00781 0.00287 -0.0390 0.9287 0.4236 -3.250 -0.2109 0.00744 0.00275 -0.0380 0.9232 0.5027 -3.000 -0.1873 0.00715 0.00265 -0.0371 0.9182 0.5661 -2.750 -0.1630 0.00692 0.00258 -0.0362 0.9143 0.6209 -2.500 -0.1386 0.00678 0.00255 -0.0355 0.9087 0.6618 -2.250 -0.1132 0.00670 0.00253 -0.0348 0.9039 0.6979 -2.000 -0.0871 0.00666 0.00251 -0.0341 0.8999 0.7246 -1.750 -0.0613 0.00662 0.00251 -0.0336 0.8940 0.7456 -1.500 -0.0351 0.00659 0.00247 -0.0330 0.8890 0.7642 -1.250 -0.0087 0.00658 0.00246 -0.0325 0.8844 0.7805 -1.000 0.0174 0.00655 0.00245 -0.0320 0.8782 0.7954 -0.750 0.0438 0.00653 0.00243 -0.0314 0.8732 0.8098 -0.500 0.0698 0.00651 0.00243 -0.0308 0.8671 0.8231 -0.250 0.0960 0.00647 0.00240 -0.0302 0.8608 0.8348 0.000 0.1224 0.00644 0.00238 -0.0297 0.8546 0.8456 0.250 0.1487 0.00640 0.00234 -0.0292 0.8469 0.8557 0.500 0.1750 0.00635 0.00231 -0.0286 0.8394 0.8641 0.750 0.2015 0.00629 0.00225 -0.0281 0.8308 0.8728 1.000 0.2275 0.00624 0.00223 -0.0275 0.8209 0.8816 1.250 0.2538 0.00619 0.00219 -0.0270 0.8109 0.8898 1.500 0.2799 0.00614 0.00213 -0.0264 0.7994 0.8989 1.750 0.3058 0.00609 0.00210 -0.0257 0.7857 0.9069 2.000 0.3316 0.00606 0.00208 -0.0251 0.7695 0.9159 2.250 0.3572 0.00606 0.00207 -0.0244 0.7498 0.9250 2.500 0.3834 0.00609 0.00206 -0.0238 0.7274 0.9337 2.750 0.4098 0.00616 0.00209 -0.0233 0.7034 0.9435 3.000 0.4384 0.00628 0.00215 -0.0234 0.6755 0.9522 3.250 0.4688 0.00643 0.00224 -0.0239 0.6450 0.9602 3.500 0.4990 0.00667 0.00234 -0.0244 0.5997 0.9687 3.750 0.5309 0.00708 0.00249 -0.0255 0.5302 0.9753 4.000 0.5614 0.00763 0.00272 -0.0265 0.4461 0.9833 4.250 0.5941 0.00848 0.00306 -0.0284 0.3273 0.9886 4.500 0.6262 0.00935 0.00345 -0.0301 0.2226 0.9951 4.750 0.6601 0.01011 0.00386 -0.0322 0.1461 1.0000 5.000 0.6729 0.01055 0.00413 -0.0297 0.1108 1.0000 5.250 0.6898 0.01100 0.00446 -0.0279 0.0863 1.0000 5.500 0.7086 0.01147 0.00481 -0.0263 0.0689 1.0000 5.750 0.7293 0.01185 0.00516 -0.0251 0.0580 1.0000 6.000 0.7508 0.01223 0.00555 -0.0241 0.0499 1.0000 6.250 0.7710 0.01278 0.00607 -0.0228 0.0423 1.0000 6.500 0.7946 0.01304 0.00639 -0.0222 0.0383 1.0000 6.750 0.8152 0.01364 0.00697 -0.0210 0.0315 1.0000 7.000 0.8372 0.01411 0.00743 -0.0201 0.0245 1.0000 7.250 0.8583 0.01470 0.00806 -0.0190 0.0197 1.0000 7.500 0.8750 0.01579 0.00918 -0.0173 0.0165 1.0000 7.750 0.8961 0.01639 0.00987 -0.0162 0.0156 1.0000 8.000 0.9162 0.01711 0.01067 -0.0150 0.0145 1.0000 8.250 0.9360 0.01787 0.01150 -0.0138 0.0135 1.0000 8.500 0.9548 0.01874 0.01243 -0.0126 0.0129 1.0000 8.750 0.9711 0.02004 0.01382 -0.0109 0.0122 1.0000 9.000 0.9839 0.02247 0.01647 -0.0089 0.0117 1.0000 9.250 1.0019 0.02385 0.01803 -0.0076 0.0114 1.0000 9.500 1.0190 0.02531 0.01968 -0.0062 0.0112 1.0000 9.750 1.0344 0.02695 0.02154 -0.0046 0.0110 1.0000 10.000 1.0495 0.02819 0.02295 -0.0031 0.0105 1.0000 10.250 1.0599 0.03024 0.02526 -0.0010 0.0103 1.0000 10.500 1.0661 0.03262 0.02792 0.0014 0.0102 1.0000 10.750 1.0653 0.03519 0.03078 0.0047 0.0101 1.0000 11.000 1.0562 0.03816 0.03406 0.0087 0.0101 1.0000 11.250 1.0449 0.04109 0.03726 0.0122 0.0101 1.0000 11.500 1.0300 0.04439 0.04082 0.0151 0.0102 1.0000 11.750 1.0152 0.04774 0.04439 0.0172 0.0100 1.0000 12.000 0.9877 0.05294 0.04986 0.0183 0.0103 1.0000 12.250 0.9644 0.05812 0.05526 0.0177 0.0103 1.0000 12.500 0.9410 0.06409 0.06141 0.0154 0.0106 1.0000 12.750 0.9125 0.07206 0.06955 0.0108 0.0108 1.0000 13.000 0.8903 0.08056 0.07820 0.0047 0.0108 1.0000 13.250 0.8592 0.09379 0.09158 -0.0050 0.0110 1.0000