XFOIL Version 6.96 Calculated polar for: LWK 80-080 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.6717 0.08298 0.07953 -0.0114 1.0000 0.0114 -9.500 -0.6847 0.07412 0.07069 -0.0195 1.0000 0.0113 -9.250 -0.7005 0.06780 0.06430 -0.0237 1.0000 0.0111 -9.000 -0.7160 0.06306 0.05946 -0.0243 1.0000 0.0110 -8.750 -0.7290 0.05807 0.05432 -0.0238 1.0000 0.0109 -8.500 -0.7381 0.05284 0.04886 -0.0227 1.0000 0.0109 -8.250 -0.7423 0.04793 0.04368 -0.0211 1.0000 0.0108 -8.000 -0.7443 0.04288 0.03826 -0.0190 1.0000 0.0106 -7.750 -0.7432 0.03791 0.03285 -0.0164 1.0000 0.0108 -7.500 -0.7371 0.03372 0.02818 -0.0139 1.0000 0.0109 -7.250 -0.7269 0.03011 0.02407 -0.0115 1.0000 0.0111 -7.000 -0.7127 0.02706 0.02051 -0.0093 1.0000 0.0119 -6.750 -0.6929 0.02584 0.01896 -0.0079 1.0000 0.0130 -6.500 -0.6768 0.02305 0.01581 -0.0061 1.0000 0.0138 -6.250 -0.6578 0.02140 0.01398 -0.0048 1.0000 0.0148 -6.000 -0.6378 0.01993 0.01233 -0.0033 1.0000 0.0155 -5.750 -0.6178 0.01869 0.01096 -0.0019 1.0000 0.0163 -5.500 -0.5987 0.01759 0.00970 -0.0003 1.0000 0.0174 -5.250 -0.5807 0.01664 0.00866 0.0015 1.0000 0.0186 -5.000 -0.5642 0.01585 0.00777 0.0035 1.0000 0.0201 -4.750 -0.5395 0.01486 0.00673 0.0037 0.9916 0.0249 -4.500 -0.5078 0.01433 0.00612 0.0026 0.9842 0.0318 -4.250 -0.4769 0.01366 0.00544 0.0015 0.9771 0.0424 -4.000 -0.4450 0.01310 0.00485 0.0003 0.9707 0.0573 -3.750 -0.4136 0.01251 0.00433 -0.0009 0.9646 0.0846 -3.500 -0.3826 0.01189 0.00390 -0.0021 0.9585 0.1310 -3.250 -0.3535 0.01108 0.00350 -0.0031 0.9525 0.2309 -3.000 -0.3310 0.00992 0.00312 -0.0028 0.9449 0.4147 -2.750 -0.3118 0.00896 0.00306 -0.0011 0.9379 0.6268 -2.500 -0.2844 0.00884 0.00313 -0.0007 0.9319 0.7091 -2.250 -0.2534 0.00884 0.00313 -0.0011 0.9275 0.7488 -2.000 -0.2264 0.00887 0.00314 -0.0007 0.9212 0.7758 -1.750 -0.1979 0.00892 0.00318 -0.0004 0.9160 0.8023 -1.500 -0.1694 0.00898 0.00324 -0.0001 0.9114 0.8253 -1.250 -0.1432 0.00902 0.00327 0.0005 0.9055 0.8422 -1.000 -0.1135 0.00904 0.00327 0.0003 0.9010 0.8540 -0.750 -0.0854 0.00904 0.00325 0.0004 0.8957 0.8622 -0.500 -0.0576 0.00904 0.00322 0.0004 0.8902 0.8693 -0.250 -0.0275 0.00903 0.00319 -0.0001 0.8860 0.8747 0.000 0.0000 0.00903 0.00319 0.0000 0.8801 0.8801 0.250 0.0275 0.00903 0.00319 0.0001 0.8747 0.8860 0.500 0.0577 0.00904 0.00322 -0.0004 0.8694 0.8902 0.750 0.0854 0.00904 0.00325 -0.0004 0.8621 0.8957 1.000 0.1134 0.00904 0.00327 -0.0003 0.8538 0.9009 1.250 0.1431 0.00902 0.00327 -0.0005 0.8419 0.9055 1.500 0.1694 0.00898 0.00324 0.0001 0.8253 0.9113 1.750 0.1979 0.00891 0.00318 0.0005 0.8015 0.9161 2.000 0.2263 0.00886 0.00314 0.0007 0.7748 0.9213 2.250 0.2534 0.00884 0.00313 0.0011 0.7486 0.9275 2.500 0.2846 0.00884 0.00315 0.0006 0.7118 0.9318 2.750 0.3122 0.00895 0.00311 0.0010 0.6329 0.9378 3.000 0.3304 0.00997 0.00313 0.0029 0.4063 0.9450 3.250 0.3529 0.01116 0.00351 0.0031 0.2179 0.9528 3.500 0.3826 0.01190 0.00390 0.0020 0.1293 0.9586 3.750 0.4137 0.01250 0.00433 0.0009 0.0853 0.9647 4.000 0.4451 0.01309 0.00486 -0.0003 0.0579 0.9707 4.250 0.4770 0.01363 0.00540 -0.0015 0.0407 0.9770 4.500 0.5080 0.01425 0.00604 -0.0026 0.0299 0.9840 4.750 0.5384 0.01508 0.00689 -0.0036 0.0218 0.9918 5.000 0.5641 0.01588 0.00781 -0.0035 0.0194 1.0000 5.250 0.5805 0.01669 0.00871 -0.0014 0.0181 1.0000 5.500 0.5985 0.01764 0.00975 0.0004 0.0165 1.0000 5.750 0.6177 0.01873 0.01100 0.0019 0.0160 1.0000 6.000 0.6375 0.01997 0.01236 0.0034 0.0150 1.0000 6.250 0.6576 0.02146 0.01403 0.0048 0.0146 1.0000 6.500 0.6765 0.02324 0.01601 0.0062 0.0138 1.0000 6.750 0.6938 0.02554 0.01867 0.0078 0.0127 1.0000 7.000 0.7121 0.02734 0.02082 0.0094 0.0119 1.0000 7.250 0.7265 0.03022 0.02418 0.0115 0.0113 1.0000 7.500 0.7368 0.03381 0.02827 0.0139 0.0110 1.0000 7.750 0.7436 0.03778 0.03270 0.0163 0.0111 1.0000 8.000 0.7465 0.04224 0.03757 0.0187 0.0110 1.0000 8.250 0.7442 0.04744 0.04315 0.0209 0.0110 1.0000 8.500 0.7375 0.05298 0.04901 0.0227 0.0109 1.0000 8.750 0.7308 0.05769 0.05392 0.0237 0.0111 1.0000 9.000 0.7188 0.06260 0.05899 0.0242 0.0111 1.0000 9.250 0.7026 0.06739 0.06388 0.0237 0.0113 1.0000 9.500 0.6866 0.07364 0.07021 0.0198 0.0115 1.0000 9.750 0.6755 0.08168 0.07825 0.0124 0.0117 1.0000 10.000 0.6664 0.08937 0.08589 0.0067 0.0117 1.0000