XFOIL Version 6.96 Calculated polar for: RAF 38 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 ------ -------- --------- --------- -------- -------- -------- -17.000 -0.8779 0.10138 0.09891 -0.0342 1.0000 0.0076 -16.750 -0.9880 0.07869 0.07592 -0.0473 1.0000 0.0071 -16.500 -1.0887 0.05683 0.05370 -0.0613 1.0000 0.0068 -16.250 -1.1299 0.04563 0.04224 -0.0701 1.0000 0.0068 -16.000 -1.1428 0.04018 0.03663 -0.0741 1.0000 0.0068 -15.750 -1.1553 0.03574 0.03204 -0.0766 1.0000 0.0068 -15.500 -1.1582 0.03304 0.02921 -0.0772 1.0000 0.0069 -15.250 -1.1639 0.03054 0.02659 -0.0768 1.0000 0.0070 -15.000 -1.1676 0.02857 0.02451 -0.0754 1.0000 0.0071 -14.750 -1.1681 0.02709 0.02293 -0.0733 1.0000 0.0072 -14.500 -1.1680 0.02583 0.02159 -0.0705 1.0000 0.0073 -14.250 -1.1662 0.02487 0.02054 -0.0673 1.0000 0.0074 -14.000 -1.1631 0.02403 0.01963 -0.0639 1.0000 0.0075 -13.750 -1.1544 0.02317 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0.750 0.3228 0.00664 0.00113 -0.0439 0.5413 0.5267 1.000 0.3482 0.00660 0.00114 -0.0434 0.5276 0.5613 1.250 0.3728 0.00656 0.00117 -0.0427 0.5114 0.6030 1.500 0.3955 0.00646 0.00122 -0.0416 0.4941 0.6708 1.750 0.4181 0.00641 0.00129 -0.0405 0.4770 0.7302 2.000 0.4401 0.00639 0.00137 -0.0392 0.4581 0.7841 2.250 0.4625 0.00637 0.00146 -0.0379 0.4426 0.8337 2.500 0.4875 0.00634 0.00156 -0.0372 0.4314 0.8840 2.750 0.5189 0.00641 0.00168 -0.0379 0.4213 0.9199 3.000 0.5566 0.00657 0.00182 -0.0400 0.4084 0.9426 3.250 0.5960 0.00673 0.00195 -0.0426 0.3968 0.9565 3.500 0.6318 0.00688 0.00207 -0.0444 0.3860 0.9652 3.750 0.6656 0.00704 0.00218 -0.0458 0.3730 0.9697 4.000 0.6951 0.00721 0.00231 -0.0462 0.3611 0.9753 4.250 0.7275 0.00740 0.00244 -0.0473 0.3461 0.9784 4.500 0.7565 0.00765 0.00260 -0.0477 0.3211 0.9828 4.750 0.7875 0.00796 0.00279 -0.0487 0.2940 0.9865 5.000 0.8198 0.00836 0.00303 -0.0500 0.2611 0.9902 5.250 0.8501 0.00883 0.00333 -0.0509 0.2279 0.9942 5.500 0.8841 0.00918 0.00358 -0.0526 0.2055 0.9969 5.750 0.9170 0.00953 0.00383 -0.0540 0.1839 0.9991 6.000 0.9424 0.00993 0.00411 -0.0539 0.1589 1.0000 6.250 0.9581 0.01040 0.00443 -0.0517 0.1292 1.0000 6.500 0.9698 0.01108 0.00488 -0.0488 0.0895 1.0000 6.750 0.9861 0.01151 0.00522 -0.0467 0.0737 1.0000 7.000 1.0042 0.01184 0.00552 -0.0450 0.0666 1.0000 7.250 1.0237 0.01209 0.00577 -0.0434 0.0634 1.0000 7.500 1.0427 0.01237 0.00604 -0.0418 0.0601 1.0000 7.750 1.0612 0.01267 0.00634 -0.0402 0.0568 1.0000 8.000 1.0805 0.01293 0.00661 -0.0387 0.0548 1.0000 8.250 1.0999 0.01317 0.00688 -0.0372 0.0528 1.0000 8.500 1.1184 0.01347 0.00717 -0.0356 0.0500 1.0000 8.750 1.1354 0.01382 0.00752 -0.0337 0.0462 1.0000 9.000 1.1534 0.01412 0.00783 -0.0321 0.0440 1.0000 9.250 1.1706 0.01445 0.00817 -0.0303 0.0402 1.0000 9.500 1.1828 0.01487 0.00855 -0.0276 0.0343 1.0000 10.000 1.2046 0.01578 0.00944 -0.0219 0.0252 1.0000 10.250 1.2156 0.01633 0.00997 -0.0193 0.0218 1.0000 10.500 1.2286 0.01685 0.01051 -0.0172 0.0199 1.0000 11.000 1.2530 0.01808 0.01178 -0.0131 0.0165 1.0000 11.250 1.2655 0.01875 0.01247 -0.0113 0.0154 1.0000 11.500 1.2769 0.01953 0.01328 -0.0095 0.0142 1.0000 11.750 1.2896 0.02028 0.01408 -0.0080 0.0136 1.0000 12.000 1.3013 0.02114 0.01497 -0.0065 0.0127 1.0000 12.250 1.3123 0.02210 0.01597 -0.0051 0.0120 1.0000 12.500 1.3227 0.02316 0.01707 -0.0038 0.0114 1.0000 12.750 1.3343 0.02417 0.01813 -0.0028 0.0109 1.0000 13.000 1.3448 0.02530 0.01931 -0.0017 0.0104 1.0000 13.250 1.3547 0.02653 0.02060 -0.0007 0.0101 1.0000 13.500 1.3634 0.02788 0.02200 0.0002 0.0098 1.0000 13.750 1.3708 0.02939 0.02356 0.0011 0.0093 1.0000 14.000 1.3788 0.03088 0.02511 0.0019 0.0090 1.0000 14.250 1.3869 0.03240 0.02669 0.0026 0.0086 1.0000 14.500 1.3931 0.03413 0.02848 0.0032 0.0084 1.0000 14.750 1.3997 0.03585 0.03027 0.0038 0.0081 1.0000 15.000 1.4044 0.03778 0.03225 0.0043 0.0079 1.0000 15.250 1.4079 0.03986 0.03440 0.0047 0.0076 1.0000 15.500 1.4107 0.04209 0.03669 0.0051 0.0075 1.0000 15.750 1.4111 0.04460 0.03928 0.0053 0.0073 1.0000 16.000 1.4139 0.04695 0.04171 0.0054 0.0071 1.0000 16.250 1.4153 0.04950 0.04435 0.0054 0.0070 1.0000 16.500 1.4161 0.05221 0.04713 0.0053 0.0069 1.0000 16.750 1.4164 0.05501 0.05002 0.0050 0.0067 1.0000 17.000 1.4157 0.05802 0.05311 0.0047 0.0066 1.0000 17.250 1.4147 0.06115 0.05632 0.0042 0.0064 1.0000 17.500 1.4125 0.06446 0.05971 0.0035 0.0063 1.0000 17.750 1.4077 0.06819 0.06353 0.0027 0.0062 1.0000 18.000 1.4045 0.07177 0.06719 0.0019 0.0061 1.0000 18.250 1.3976 0.07595 0.07147 0.0008 0.0060 1.0000 18.500 1.3924 0.07991 0.07551 -0.0004 0.0059 1.0000 18.750 1.3829 0.08458 0.08027 -0.0018 0.0058 1.0000 19.000 1.3735 0.08933 0.08512 -0.0033 0.0057 1.0000 19.250 1.3602 0.09473 0.09062 -0.0052 0.0056 1.0000