XFOIL Version 6.94 Calculated polar for: S3014-095-85 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3026 0.00610 0.00195 -0.0548 0.7484 0.9993 0.500 0.3540 0.00612 0.00181 -0.0538 0.7254 1.0000 1.000 0.4043 0.00619 0.00173 -0.0525 0.6999 1.0000 1.500 0.4549 0.00632 0.00170 -0.0512 0.6717 1.0000 2.000 0.5057 0.00649 0.00172 -0.0500 0.6396 1.0000 2.500 0.5566 0.00672 0.00181 -0.0488 0.6033 1.0000 3.000 0.6071 0.00703 0.00195 -0.0476 0.5622 1.0000 3.500 0.6573 0.00739 0.00217 -0.0465 0.5165 1.0000 4.000 0.7066 0.00786 0.00244 -0.0452 0.4649 1.0000 4.500 0.7553 0.00842 0.00281 -0.0439 0.4099 1.0000 5.000 0.8032 0.00908 0.00324 -0.0426 0.3529 1.0000 5.500 0.8506 0.00979 0.00375 -0.0413 0.3025 1.0000 6.000 0.8984 0.01049 0.00435 -0.0400 0.2614 1.0000 6.500 0.9457 0.01122 0.00497 -0.0387 0.2253 1.0000 7.000 0.9918 0.01205 0.00567 -0.0373 0.1829 1.0000 7.500 1.0370 0.01294 0.00642 -0.0359 0.1451 1.0000 8.000 1.0809 0.01391 0.00727 -0.0342 0.1125 1.0000 8.500 1.1231 0.01499 0.00825 -0.0324 0.0818 1.0000 9.000 1.1548 0.01697 0.00988 -0.0293 0.0261 1.0000 9.500 1.1837 0.01905 0.01191 -0.0256 0.0109 1.0000 10.000 1.2117 0.02090 0.01402 -0.0218 0.0093 1.0000 10.500 1.2297 0.02280 0.01615 -0.0165 0.0086 1.0000 11.000 1.2401 0.02523 0.01880 -0.0113 0.0081 1.0000 11.500 1.2462 0.02830 0.02214 -0.0068 0.0077 1.0000 12.000 1.2481 0.03212 0.02621 -0.0031 0.0075 1.0000 12.500 1.2457 0.03682 0.03116 -0.0006 0.0072 1.0000 13.000 1.2376 0.04270 0.03731 0.0009 0.0070 1.0000 13.500 1.2330 0.04877 0.04367 0.0012 0.0071 1.0000 14.000 1.2207 0.05640 0.05161 0.0002 0.0070 1.0000 14.500 1.2077 0.06486 0.06040 -0.0021 0.0071 1.0000 15.000 1.1888 0.07509 0.07096 -0.0060 0.0071 1.0000 15.500 1.1634 0.08742 0.08366 -0.0118 0.0073 1.0000 16.000 1.1335 0.10176 0.09836 -0.0193 0.0075 1.0000 16.500 1.1010 0.11786 0.11478 -0.0284 0.0076 1.0000 17.000 1.0639 0.13644 0.13368 -0.0393 0.0079 1.0000 17.500 1.0214 0.15834 0.15585 -0.0521 0.0082 1.0000 18.000 0.9402 0.19802 0.19566 -0.0721 0.0095 1.0000