XFOIL Version 6.96 Calculated polar for: S4158 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.2948 0.08448 0.08184 -0.0586 0.8618 0.0216 -8.750 -0.2939 0.08041 0.07780 -0.0613 0.8597 0.0217 -8.500 -0.2940 0.07612 0.07353 -0.0642 0.8572 0.0217 -8.250 -0.3137 0.06927 0.06675 -0.0681 0.8539 0.0222 -8.000 -0.3221 0.06394 0.06140 -0.0729 0.8507 0.0222 -7.750 -0.3190 0.06079 0.05822 -0.0744 0.8486 0.0226 -7.500 -0.3126 0.05821 0.05558 -0.0756 0.8466 0.0230 -7.250 -0.3029 0.05542 0.05276 -0.0773 0.8445 0.0236 -7.000 -0.2943 0.05156 0.04881 -0.0795 0.8419 0.0242 -6.750 -0.2838 0.04770 0.04482 -0.0812 0.8394 0.0252 -6.500 -0.2724 0.04322 0.04012 -0.0824 0.8371 0.0267 -6.250 -0.2537 0.04040 0.03679 -0.0823 0.8350 0.0287 -6.000 -0.2526 0.03308 0.02904 -0.0823 0.8330 0.0299 -5.750 -0.2318 0.03114 0.02706 -0.0824 0.8311 0.0307 -5.500 -0.2099 0.02937 0.02518 -0.0825 0.8289 0.0317 -5.250 -0.1984 0.01855 0.01280 -0.0785 0.8262 0.0172 -5.000 -0.1733 0.01714 0.01117 -0.0781 0.8242 0.0175 -4.750 -0.1477 0.01612 0.01000 -0.0776 0.8223 0.0178 -4.500 -0.1219 0.01526 0.00903 -0.0772 0.8205 0.0182 -4.250 -0.0963 0.01452 0.00818 -0.0767 0.8189 0.0186 -4.000 -0.0699 0.01398 0.00758 -0.0764 0.8170 0.0195 -3.750 -0.0426 0.01355 0.00711 -0.0764 0.8143 0.0207 -3.500 -0.0159 0.01305 0.00655 -0.0762 0.8117 0.0213 -3.250 0.0101 0.01245 0.00589 -0.0758 0.8092 0.0222 -3.000 0.0360 0.01189 0.00528 -0.0753 0.8071 0.0246 -2.750 0.0629 0.01159 0.00492 -0.0750 0.8052 0.0281 -2.500 0.0890 0.01111 0.00451 -0.0745 0.8031 0.0526 -2.250 0.1160 0.01074 0.00437 -0.0746 0.7998 0.1021 -2.000 0.1426 0.01038 0.00421 -0.0745 0.7967 0.1619 -1.750 0.1681 0.00988 0.00406 -0.0743 0.7939 0.2673 -1.500 0.1926 0.00928 0.00392 -0.0739 0.7915 0.4128 -1.250 0.2156 0.00870 0.00384 -0.0730 0.7893 0.5731 -1.000 0.2376 0.00821 0.00386 -0.0718 0.7851 0.7177 -0.750 0.2603 0.00782 0.00381 -0.0703 0.7813 0.8290 -0.500 0.3053 0.00755 0.00373 -0.0733 0.7787 0.9411 -0.250 0.3579 0.00748 0.00358 -0.0783 0.7766 0.9761 0.000 0.4048 0.00745 0.00345 -0.0822 0.7746 0.9928 0.250 0.4492 0.00740 0.00339 -0.0860 0.7707 1.0000 0.500 0.4744 0.00737 0.00332 -0.0855 0.7665 1.0000 0.750 0.4998 0.00732 0.00321 -0.0849 0.7632 1.0000 1.000 0.5254 0.00727 0.00309 -0.0844 0.7603 1.0000 1.250 0.5513 0.00728 0.00311 -0.0841 0.7550 1.0000 1.500 0.5773 0.00723 0.00303 -0.0837 0.7505 1.0000 1.750 0.6035 0.00716 0.00292 -0.0832 0.7468 1.0000 2.000 0.6296 0.00715 0.00292 -0.0829 0.7408 1.0000 2.250 0.6558 0.00707 0.00281 -0.0825 0.7349 1.0000 2.500 0.6820 0.00699 0.00273 -0.0821 0.7273 1.0000 2.750 0.7083 0.00690 0.00262 -0.0816 0.7192 1.0000 3.000 0.7345 0.00688 0.00261 -0.0813 0.7097 1.0000 3.250 0.7608 0.00686 0.00258 -0.0810 0.7006 1.0000 3.500 0.7870 0.00686 0.00254 -0.0806 0.6904 1.0000 3.750 0.8131 0.00689 0.00258 -0.0802 0.6778 1.0000 4.000 0.8388 0.00695 0.00261 -0.0798 0.6638 1.0000 4.250 0.8641 0.00705 0.00265 -0.0793 0.6484 1.0000 4.500 0.8892 0.00718 0.00277 -0.0788 0.6311 1.0000 4.750 0.9138 0.00736 0.00289 -0.0782 0.6115 1.0000 5.000 0.9372 0.00762 0.00304 -0.0774 0.5852 1.0000 5.250 0.9593 0.00795 0.00324 -0.0765 0.5528 1.0000 5.500 0.9809 0.00832 0.00349 -0.0755 0.5213 1.0000 5.750 1.0013 0.00875 0.00379 -0.0743 0.4867 1.0000 6.000 1.0212 0.00920 0.00411 -0.0731 0.4537 1.0000 6.250 1.0404 0.00968 0.00446 -0.0718 0.4214 1.0000 6.500 1.0582 0.01022 0.00485 -0.0703 0.3879 1.0000 6.750 1.0757 0.01076 0.00526 -0.0687 0.3539 1.0000 7.000 1.0913 0.01137 0.00571 -0.0669 0.3178 1.0000 7.250 1.1050 0.01205 0.00620 -0.0649 0.2780 1.0000 7.500 1.1173 0.01277 0.00674 -0.0626 0.2426 1.0000 7.750 1.1283 0.01346 0.00728 -0.0600 0.2120 1.0000 8.000 1.1367 0.01416 0.00787 -0.0571 0.1862 1.0000 8.250 1.1465 0.01491 0.00849 -0.0546 0.1615 1.0000 8.500 1.1576 0.01566 0.00915 -0.0524 0.1373 1.0000 8.750 1.1679 0.01653 0.00988 -0.0502 0.1122 1.0000 9.000 1.1776 0.01748 0.01069 -0.0480 0.0889 1.0000 9.250 1.1877 0.01844 0.01155 -0.0459 0.0721 1.0000 9.750 1.2114 0.02022 0.01330 -0.0424 0.0535 1.0000 10.000 1.2212 0.02128 0.01432 -0.0404 0.0466 1.0000 10.250 1.2356 0.02203 0.01514 -0.0391 0.0432 1.0000 10.500 1.2473 0.02300 0.01612 -0.0375 0.0393 1.0000 10.750 1.2553 0.02424 0.01741 -0.0356 0.0356 1.0000 11.000 1.2691 0.02508 0.01832 -0.0343 0.0333 1.0000 11.250 1.2803 0.02613 0.01941 -0.0329 0.0306 1.0000 11.500 1.2819 0.02792 0.02124 -0.0306 0.0276 1.0000 11.750 1.2964 0.02876 0.02217 -0.0296 0.0261 1.0000 12.000 1.3072 0.02989 0.02336 -0.0283 0.0242 1.0000 12.250 1.3158 0.03122 0.02472 -0.0269 0.0225 1.0000 12.500 1.3127 0.03355 0.02713 -0.0247 0.0209 1.0000 12.750 1.3218 0.03491 0.02860 -0.0235 0.0199 1.0000 13.000 1.3304 0.03634 0.03012 -0.0224 0.0188 1.0000 13.250 1.3375 0.03793 0.03178 -0.0213 0.0177 1.0000 13.500 1.3428 0.03973 0.03365 -0.0202 0.0166 1.0000 13.750 1.3416 0.04222 0.03621 -0.0190 0.0156 1.0000 14.000 1.3391 0.04499 0.03910 -0.0177 0.0150 1.0000 14.250 1.3455 0.04689 0.04112 -0.0171 0.0145 1.0000 14.500 1.3499 0.04909 0.04343 -0.0165 0.0141 1.0000 14.750 1.3523 0.05156 0.04602 -0.0160 0.0135 1.0000 15.000 1.3549 0.05410 0.04866 -0.0156 0.0131 1.0000 15.250 1.3569 0.05676 0.05141 -0.0155 0.0126 1.0000 15.500 1.3573 0.05969 0.05444 -0.0155 0.0122 1.0000 15.750 1.3564 0.06288 0.05770 -0.0157 0.0117 1.0000 16.000 1.3486 0.06701 0.06194 -0.0159 0.0112 1.0000 16.250 1.3409 0.07129 0.06637 -0.0163 0.0109 1.0000 16.500 1.3382 0.07508 0.07031 -0.0170 0.0108 1.0000 16.750 1.3363 0.07893 0.07433 -0.0180 0.0105 1.0000 17.000 1.3320 0.08315 0.07870 -0.0192 0.0104 1.0000 17.250 1.3270 0.08763 0.08332 -0.0207 0.0102 1.0000 17.500 1.3212 0.09237 0.08821 -0.0225 0.0099 1.0000 17.750 1.3119 0.09779 0.09379 -0.0244 0.0099 1.0000 18.000 1.3036 0.10322 0.09936 -0.0268 0.0097 1.0000 18.250 1.2943 0.10896 0.10526 -0.0295 0.0095 1.0000 18.500 1.2842 0.11501 0.11145 -0.0324 0.0094 1.0000 18.750 1.2716 0.12167 0.11827 -0.0358 0.0094 1.0000 19.000 1.2613 0.12811 0.12485 -0.0393 0.0092 1.0000 19.250 1.2478 0.13533 0.13222 -0.0434 0.0092 1.0000