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 = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3436 0.10454 0.09932 -0.0378 1.0000 0.1672 -10.250 -0.5442 0.06993 0.06484 -0.0655 1.0000 0.1010 -10.000 -0.5590 0.06658 0.06154 -0.0635 1.0000 0.1004 -9.750 -0.5850 0.06427 0.05930 -0.0593 1.0000 0.0998 -9.500 -0.6167 0.06301 0.05811 -0.0533 1.0000 0.0992 -9.250 -0.6503 0.06205 0.05718 -0.0468 1.0000 0.0984 -9.000 -0.6832 0.06021 0.05529 -0.0412 1.0000 0.0976 -8.750 -0.7133 0.05741 0.05235 -0.0363 1.0000 0.0966 -8.500 -0.7121 0.05088 0.04525 -0.0387 0.9907 0.0967 -8.250 -0.7015 0.04575 0.03953 -0.0402 0.9825 0.0973 -8.000 -0.6898 0.04191 0.03514 -0.0401 0.9739 0.0985 -7.750 -0.6721 0.03886 0.03135 -0.0402 0.9665 0.1011 -7.500 -0.6486 0.03642 0.02873 -0.0408 0.9592 0.1038 -7.250 -0.6124 0.03476 0.02694 -0.0432 0.9545 0.1076 -7.000 -0.5937 0.03340 0.02527 -0.0422 0.9458 0.1115 -6.750 -0.5613 0.03156 0.02303 -0.0436 0.9404 0.1165 -6.500 -0.5354 0.03056 0.02201 -0.0437 0.9330 0.1213 -6.250 -0.5047 0.02958 0.02066 -0.0444 0.9264 0.1286 -6.000 -0.4604 0.02821 0.01938 -0.0478 0.9226 0.1380 -5.750 -0.4422 0.02742 0.01843 -0.0462 0.9129 0.1461 -5.500 -0.3989 0.02640 0.01736 -0.0491 0.9078 0.1611 -5.250 -0.3731 0.02584 0.01675 -0.0488 0.8991 0.1755 -5.000 -0.3339 0.02488 0.01595 -0.0511 0.8930 0.1957 -4.750 -0.2865 0.02405 0.01518 -0.0546 0.8892 0.2224 -4.500 -0.2729 0.02384 0.01502 -0.0521 0.8785 0.2390 -4.250 -0.2318 0.02312 0.01440 -0.0545 0.8737 0.2660 -4.000 -0.2150 0.02292 0.01428 -0.0525 0.8642 0.2871 -3.750 -0.1811 0.02230 0.01380 -0.0535 0.8582 0.3191 -3.500 -0.1566 0.02186 0.01355 -0.0528 0.8507 0.3537 -3.250 -0.1342 0.02140 0.01333 -0.0516 0.8424 0.3979 -3.000 -0.1006 0.02059 0.01294 -0.0520 0.8378 0.4713 -2.750 -0.0939 0.02042 0.01318 -0.0480 0.8265 0.5410 -2.500 -0.0610 0.01981 0.01314 -0.0473 0.8216 0.6661 -2.250 -0.0404 0.01999 0.01357 -0.0449 0.8118 0.7513 -2.000 0.0057 0.02000 0.01362 -0.0463 0.8063 0.8214 -1.750 0.0701 0.02005 0.01355 -0.0510 0.8026 0.8673 -1.500 0.1220 0.02053 0.01394 -0.0545 0.7928 0.8970 -1.250 0.2063 0.02062 0.01382 -0.0633 0.7878 0.9161 -1.000 0.2739 0.02083 0.01389 -0.0699 0.7796 0.9355 -0.750 0.3370 0.02085 0.01376 -0.0758 0.7717 0.9566 -0.500 0.4038 0.02068 0.01345 -0.0831 0.7630 0.9734 -0.250 0.4653 0.02025 0.01290 -0.0896 0.7535 0.9890 0.000 0.5131 0.01994 0.01252 -0.0941 0.7430 1.0000 0.250 0.5311 0.01984 0.01231 -0.0926 0.7344 1.0000 0.500 0.5436 0.02003 0.01248 -0.0905 0.7229 1.0000 0.750 0.5644 0.01988 0.01221 -0.0891 0.7155 1.0000 1.000 0.5760 0.02015 0.01249 -0.0869 0.7035 1.0000 1.250 0.5949 0.02016 0.01242 -0.0853 0.6954 1.0000 1.500 0.6094 0.02036 0.01260 -0.0833 0.6850 1.0000 1.750 0.6268 0.02049 0.01268 -0.0816 0.6764 1.0000 2.000 0.6431 0.02065 0.01282 -0.0797 0.6672 1.0000 2.250 0.6601 0.02086 0.01300 -0.0779 0.6590 1.0000 2.500 0.6766 0.02106 0.01317 -0.0760 0.6501 1.0000 2.750 0.6949 0.02125 0.01333 -0.0743 0.6425 1.0000 3.000 0.7102 0.02154 0.01362 -0.0722 0.6336 1.0000 3.250 0.7324 0.02159 0.01361 -0.0710 0.6270 1.0000 3.500 0.7452 0.02202 0.01407 -0.0686 0.6174 1.0000 3.750 0.7727 0.02184 0.01380 -0.0679 0.6115 1.0000 4.000 0.7824 0.02242 0.01446 -0.0651 0.6011 1.0000 4.250 0.8128 0.02213 0.01406 -0.0648 0.5953 1.0000 4.500 0.8217 0.02278 0.01481 -0.0619 0.5848 1.0000 4.750 0.8532 0.02247 0.01439 -0.0618 0.5787 1.0000 5.000 0.8626 0.02312 0.01514 -0.0589 0.5683 1.0000 5.250 0.8956 0.02275 0.01467 -0.0590 0.5619 1.0000 5.500 0.9051 0.02340 0.01543 -0.0561 0.5514 1.0000 5.750 0.9353 0.02318 0.01514 -0.0559 0.5442 1.0000 6.000 0.9490 0.02363 0.01568 -0.0535 0.5339 1.0000 6.250 0.9732 0.02368 0.01572 -0.0525 0.5253 1.0000 6.500 0.9946 0.02381 0.01586 -0.0511 0.5157 1.0000 6.750 1.0129 0.02411 0.01622 -0.0493 0.5057 1.0000 7.000 1.0434 0.02393 0.01595 -0.0492 0.4967 1.0000 7.250 1.0561 0.02443 0.01657 -0.0466 0.4854 1.0000 7.500 1.0794 0.02457 0.01671 -0.0455 0.4751 1.0000 7.750 1.1049 0.02462 0.01671 -0.0448 0.4642 1.0000 8.000 1.1184 0.02509 0.01727 -0.0423 0.4519 1.0000 8.250 1.1382 0.02538 0.01758 -0.0407 0.4399 1.0000 8.500 1.1643 0.02553 0.01766 -0.0401 0.4280 1.0000 8.750 1.1807 0.02590 0.01807 -0.0380 0.4148 1.0000 9.000 1.1926 0.02643 0.01867 -0.0354 0.4013 1.0000 9.250 1.2068 0.02683 0.01912 -0.0331 0.3874 1.0000 9.500 1.2209 0.02713 0.01940 -0.0306 0.3729 1.0000 9.750 1.2326 0.02736 0.01961 -0.0279 0.3581 1.0000 10.000 1.2411 0.02757 0.01980 -0.0246 0.3432 1.0000 10.250 1.2474 0.02785 0.02004 -0.0212 0.3288 1.0000 10.500 1.2536 0.02824 0.02040 -0.0178 0.3153 1.0000 10.750 1.2498 0.02897 0.02121 -0.0131 0.3034 1.0000 11.000 1.2506 0.02970 0.02196 -0.0094 0.2917 1.0000 11.250 1.2547 0.03045 0.02267 -0.0063 0.2802 1.0000 11.500 1.2610 0.03123 0.02335 -0.0037 0.2684 1.0000 11.750 1.2579 0.03245 0.02469 -0.0005 0.2570 1.0000 12.000 1.2586 0.03370 0.02597 0.0021 0.2456 1.0000 12.250 1.2608 0.03497 0.02720 0.0043 0.2342 1.0000 12.500 1.2634 0.03628 0.02842 0.0063 0.2222 1.0000 12.750 1.2570 0.03817 0.03043 0.0086 0.2108 1.0000 13.000 1.2525 0.04014 0.03244 0.0105 0.1986 1.0000 13.250 1.2469 0.04231 0.03459 0.0122 0.1860 1.0000 13.500 1.2395 0.04473 0.03698 0.0137 0.1729 1.0000 13.750 1.2315 0.04737 0.03958 0.0150 0.1597 1.0000 14.000 1.2245 0.05009 0.04221 0.0161 0.1470 1.0000 14.250 1.2184 0.05286 0.04491 0.0170 0.1355 1.0000 14.500 1.2107 0.05602 0.04815 0.0176 0.1257 1.0000 14.750 1.2098 0.05864 0.05074 0.0183 0.1176 1.0000 15.000 1.2113 0.06102 0.05305 0.0188 0.1103 1.0000 15.250 1.2109 0.06383 0.05597 0.0192 0.1046 1.0000 15.500 1.2130 0.06626 0.05839 0.0195 0.0991 1.0000 15.750 1.2179 0.06865 0.06082 0.0200 0.0945 1.0000 16.000 1.2159 0.07180 0.06415 0.0199 0.0909 1.0000 16.250 1.2296 0.07307 0.06525 0.0206 0.0863 1.0000 16.500 1.2261 0.07659 0.06896 0.0205 0.0837 1.0000 16.750 1.2181 0.08066 0.07327 0.0198 0.0815 1.0000 17.000 1.2147 0.08422 0.07698 0.0194 0.0792 1.0000 17.250 1.2406 0.08435 0.07684 0.0208 0.0751 1.0000 17.500 1.2239 0.08956 0.08236 0.0193 0.0743 1.0000 17.750 1.2019 0.09576 0.08887 0.0172 0.0733 1.0000 18.000 1.1801 0.10229 0.09567 0.0147 0.0728 1.0000 18.250 1.1513 0.11031 0.10396 0.0111 0.0726 1.0000 18.500 1.1128 0.12051 0.11444 0.0058 0.0730 1.0000 18.750 1.0621 0.13399 0.12818 -0.0016 0.0743 1.0000