XFOIL Version 6.96 Calculated polar for: RAF-48 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.9800 0.09693 0.09403 -0.0456 1.0000 0.0131 -18.500 -1.0564 0.08123 0.07810 -0.0548 1.0000 0.0128 -18.250 -1.1308 0.06614 0.06274 -0.0639 1.0000 0.0125 -18.000 -1.1743 0.05560 0.05198 -0.0707 1.0000 0.0122 -17.750 -1.2031 0.04764 0.04383 -0.0761 1.0000 0.0125 -17.500 -1.2192 0.04205 0.03810 -0.0797 1.0000 0.0126 -17.250 -1.2276 0.03803 0.03395 -0.0818 1.0000 0.0126 -17.000 -1.2312 0.03497 0.03078 -0.0829 1.0000 0.0129 -16.750 -1.2331 0.03239 0.02810 -0.0834 1.0000 0.0132 -16.500 -1.2324 0.03029 0.02591 -0.0832 1.0000 0.0133 -16.250 -1.2298 0.02855 0.02409 -0.0825 1.0000 0.0135 -16.000 -1.2257 0.02708 0.02253 -0.0815 1.0000 0.0138 -15.750 -1.2202 0.02582 0.02120 -0.0801 1.0000 0.0140 -15.500 -1.2153 0.02464 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0.5118 0.3460 0.250 0.2782 0.00747 0.00146 -0.0396 0.4889 0.4360 0.500 0.3025 0.00741 0.00148 -0.0388 0.4792 0.4742 0.750 0.3266 0.00738 0.00150 -0.0380 0.4692 0.5089 1.000 0.3501 0.00727 0.00153 -0.0371 0.4607 0.5568 1.250 0.3721 0.00718 0.00157 -0.0358 0.4523 0.6144 1.500 0.3950 0.00708 0.00162 -0.0347 0.4457 0.6660 1.750 0.4175 0.00704 0.00168 -0.0335 0.4382 0.7094 2.000 0.4406 0.00702 0.00175 -0.0324 0.4309 0.7444 2.250 0.4624 0.00700 0.00183 -0.0311 0.4222 0.7856 2.500 0.4856 0.00703 0.00191 -0.0300 0.4149 0.8158 2.750 0.5105 0.00706 0.00198 -0.0293 0.4088 0.8355 3.000 0.5348 0.00712 0.00207 -0.0285 0.4018 0.8570 3.250 0.5615 0.00713 0.00214 -0.0282 0.3965 0.8777 3.500 0.5926 0.00717 0.00223 -0.0288 0.3907 0.8993 3.750 0.6423 0.00730 0.00240 -0.0338 0.3829 0.9211 4.000 0.7066 0.00747 0.00256 -0.0419 0.3731 0.9340 4.250 0.7545 0.00766 0.00272 -0.0464 0.3654 0.9431 4.500 0.7937 0.00783 0.00288 -0.0489 0.3577 0.9522 4.750 0.8244 0.00802 0.00304 -0.0496 0.3512 0.9641 5.000 0.8517 0.00816 0.00318 -0.0495 0.3454 0.9748 5.500 0.9131 0.00852 0.00350 -0.0509 0.3293 0.9859 5.750 0.9447 0.00874 0.00366 -0.0519 0.3170 0.9890 6.000 0.9739 0.00902 0.00387 -0.0525 0.2989 0.9921 6.250 1.0032 0.00936 0.00411 -0.0532 0.2777 0.9944 6.500 1.0335 0.00975 0.00437 -0.0541 0.2556 0.9966 6.750 1.0635 0.01017 0.00467 -0.0551 0.2327 0.9986 7.000 1.0935 0.01055 0.00497 -0.0560 0.2155 1.0000 7.250 1.1101 0.01089 0.00524 -0.0540 0.2022 1.0000 7.500 1.1268 0.01121 0.00552 -0.0520 0.1913 1.0000 7.750 1.1425 0.01157 0.00582 -0.0498 0.1796 1.0000 8.000 1.1584 0.01191 0.00611 -0.0477 0.1691 1.0000 8.250 1.1737 0.01225 0.00642 -0.0454 0.1593 1.0000 8.500 1.1871 0.01266 0.00677 -0.0429 0.1483 1.0000 8.750 1.2006 0.01302 0.00711 -0.0404 0.1403 1.0000 9.000 1.2108 0.01334 0.00741 -0.0372 0.1341 1.0000 9.250 1.2194 0.01367 0.00773 -0.0337 0.1276 1.0000 9.500 1.2292 0.01405 0.00809 -0.0306 0.1214 1.0000 9.750 1.2385 0.01450 0.00852 -0.0276 0.1136 1.0000 10.000 1.2490 0.01499 0.00899 -0.0249 0.1064 1.0000 10.250 1.2575 0.01561 0.00957 -0.0221 0.0976 1.0000 10.500 1.2652 0.01636 0.01027 -0.0194 0.0865 1.0000 10.750 1.2692 0.01736 0.01118 -0.0165 0.0707 1.0000 11.500 1.2894 0.02051 0.01425 -0.0101 0.0463 1.0000 11.750 1.2978 0.02161 0.01534 -0.0084 0.0421 1.0000 12.000 1.3088 0.02259 0.01636 -0.0071 0.0398 1.0000 12.500 1.3282 0.02486 0.01867 -0.0047 0.0357 1.0000 12.750 1.3384 0.02602 0.01987 -0.0037 0.0343 1.0000 13.000 1.3469 0.02735 0.02121 -0.0026 0.0326 1.0000 13.250 1.3553 0.02871 0.02261 -0.0017 0.0315 1.0000 13.500 1.3645 0.03004 0.02398 -0.0008 0.0304 1.0000 13.750 1.3726 0.03149 0.02547 0.0000 0.0292 1.0000 14.000 1.3795 0.03306 0.02709 0.0008 0.0281 1.0000 14.250 1.3857 0.03473 0.02879 0.0015 0.0272 1.0000 14.500 1.3918 0.03644 0.03055 0.0022 0.0263 1.0000 14.750 1.3988 0.03814 0.03230 0.0027 0.0256 1.0000 15.000 1.4044 0.03999 0.03421 0.0032 0.0248 1.0000 15.250 1.4085 0.04203 0.03629 0.0036 0.0236 1.0000 15.500 1.4124 0.04414 0.03845 0.0040 0.0230 1.0000 15.750 1.4159 0.04634 0.04070 0.0043 0.0220 1.0000 16.000 1.4195 0.04858 0.04300 0.0044 0.0214 1.0000 16.250 1.4222 0.05097 0.04545 0.0045 0.0207 1.0000 16.500 1.4228 0.05364 0.04816 0.0045 0.0195 1.0000 16.750 1.4239 0.05631 0.05089 0.0044 0.0191 1.0000 17.000 1.4248 0.05903 0.05367 0.0042 0.0183 1.0000 17.250 1.4251 0.06188 0.05659 0.0040 0.0177 1.0000 17.500 1.4239 0.06497 0.05974 0.0036 0.0168 1.0000 17.750 1.4211 0.06830 0.06313 0.0031 0.0160 1.0000 18.000 1.4182 0.07168 0.06657 0.0025 0.0156 1.0000 18.250 1.4161 0.07500 0.06997 0.0018 0.0152 1.0000 18.500 1.4131 0.07848 0.07352 0.0011 0.0147 1.0000 18.750 1.4090 0.08217 0.07728 0.0003 0.0142 1.0000 19.000 1.4038 0.08601 0.08119 -0.0007 0.0139 1.0000 19.250 1.3975 0.09005 0.08530 -0.0018 0.0134 1.0000