XFOIL Version 6.96 Calculated polar for: RONCZ LOW DRAG FLYING WING 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.5998 0.13231 0.12976 0.0360 0.6748 0.0048 -11.000 -0.5988 0.12770 0.12515 0.0340 0.6741 0.0048 -9.500 -0.9160 0.02970 0.02560 0.0051 0.6720 0.0058 -9.250 -0.9042 0.02667 0.02220 0.0069 0.6714 0.0059 -9.000 -0.8866 0.02476 0.02003 0.0081 0.6707 0.0059 -8.750 -0.8735 0.02176 0.01659 0.0100 0.6699 0.0061 -8.500 -0.8521 0.02045 0.01508 0.0108 0.6690 0.0063 -8.250 -0.8288 0.01951 0.01401 0.0114 0.6680 0.0064 -8.000 -0.8044 0.01875 0.01313 0.0118 0.6670 0.0066 -7.750 -0.7796 0.01805 0.01232 0.0122 0.6659 0.0067 -7.500 -0.7544 0.01739 0.01156 0.0125 0.6649 0.0068 -7.250 -0.7290 0.01675 0.01082 0.0128 0.6640 0.0070 -7.000 -0.7032 0.01616 0.01012 0.0131 0.6632 0.0072 -6.750 -0.6771 0.01562 0.00949 0.0133 0.6623 0.0075 -6.500 -0.6508 0.01511 0.00889 0.0135 0.6615 0.0078 -6.250 -0.6244 0.01460 0.00829 0.0137 0.6606 0.0080 -6.000 -0.5979 0.01410 0.00768 0.0138 0.6598 0.0082 -5.750 -0.5712 0.01365 0.00715 0.0140 0.6589 0.0084 -5.500 -0.5445 0.01319 0.00661 0.0141 0.6580 0.0085 -5.250 -0.5184 0.01258 0.00592 0.0144 0.6573 0.0089 -5.000 -0.4914 0.01218 0.00550 0.0145 0.6566 0.0092 -4.750 -0.4640 0.01186 0.00514 0.0145 0.6558 0.0095 -4.500 -0.4364 0.01156 0.00482 0.0145 0.6549 0.0099 -4.250 -0.4088 0.01127 0.00450 0.0145 0.6540 0.0103 -4.000 -0.3811 0.01100 0.00420 0.0144 0.6531 0.0107 -3.750 -0.3532 0.01076 0.00392 0.0144 0.6523 0.0112 -3.500 -0.3253 0.01053 0.00367 0.0143 0.6515 0.0118 -3.250 -0.2975 0.01025 0.00339 0.0142 0.6506 0.0129 -3.000 -0.2693 0.01005 0.00319 0.0141 0.6498 0.0138 -2.750 -0.2411 0.00987 0.00299 0.0140 0.6490 0.0149 -2.500 -0.2127 0.00971 0.00280 0.0138 0.6482 0.0158 -2.250 -0.1845 0.00951 0.00262 0.0137 0.6474 0.0179 -2.000 -0.1560 0.00937 0.00247 0.0135 0.6465 0.0199 -1.750 -0.1275 0.00923 0.00233 0.0133 0.6456 0.0228 -1.500 -0.0990 0.00910 0.00221 0.0130 0.6447 0.0269 -1.250 -0.0705 0.00898 0.00211 0.0128 0.6439 0.0335 -1.000 -0.0420 0.00885 0.00202 0.0126 0.6431 0.0442 -0.750 -0.0135 0.00868 0.00194 0.0123 0.6425 0.0637 -0.500 0.0146 0.00845 0.00186 0.0121 0.6417 0.1091 -0.250 0.0421 0.00813 0.00179 0.0119 0.6409 0.1859 0.000 0.0692 0.00776 0.00173 0.0118 0.6399 0.2808 0.250 0.0938 0.00706 0.00164 0.0120 0.6389 0.4717 0.500 0.1065 0.00551 0.00155 0.0151 0.6380 0.8679 0.750 0.1303 0.00562 0.00183 0.0165 0.6371 0.9457 1.000 0.1577 0.00590 0.00212 0.0172 0.6361 0.9670 1.250 0.1956 0.00610 0.00231 0.0151 0.6351 0.9743 1.500 0.2331 0.00617 0.00236 0.0129 0.6340 0.9757 1.750 0.2644 0.00617 0.00232 0.0120 0.6322 0.9764 2.000 0.2952 0.00617 0.00228 0.0113 0.6294 0.9770 2.250 0.3259 0.00614 0.00227 0.0105 0.6263 0.9778 2.500 0.3565 0.00613 0.00226 0.0098 0.6234 0.9786 2.750 0.3866 0.00612 0.00226 0.0091 0.6208 0.9795 3.000 0.4160 0.00610 0.00220 0.0087 0.6162 0.9805 3.250 0.4447 0.00606 0.00218 0.0083 0.6081 0.9816 3.500 0.4716 0.00606 0.00215 0.0084 0.6008 0.9832 3.750 0.5002 0.00606 0.00218 0.0081 0.5938 0.9842 4.000 0.5315 0.00607 0.00218 0.0071 0.5856 0.9844 4.250 0.5628 0.00610 0.00219 0.0062 0.5724 0.9847 4.500 0.5940 0.00618 0.00223 0.0052 0.5521 0.9850 4.750 0.6251 0.00671 0.00246 0.0037 0.4774 0.9852 5.000 0.6562 0.00744 0.00288 0.0020 0.4069 0.9855 5.250 0.6870 0.00808 0.00328 0.0004 0.3495 0.9858 5.500 0.7171 0.00887 0.00377 -0.0013 0.2810 0.9862 5.750 0.7466 0.00959 0.00422 -0.0028 0.2239 0.9866 6.000 0.7758 0.01016 0.00462 -0.0041 0.1856 0.9871 6.250 0.8047 0.01066 0.00499 -0.0052 0.1568 0.9877 6.500 0.8329 0.01122 0.00541 -0.0063 0.1267 0.9883 6.750 0.8614 0.01166 0.00577 -0.0073 0.1080 0.9891 7.000 0.8895 0.01213 0.00617 -0.0083 0.0913 0.9899 7.250 0.9167 0.01264 0.00660 -0.0091 0.0759 0.9908 7.750 0.9685 0.01366 0.00750 -0.0104 0.0519 0.9928 8.000 0.9932 0.01415 0.00798 -0.0107 0.0441 0.9939 8.250 1.0191 0.01467 0.00848 -0.0115 0.0379 0.9946 8.500 1.0463 0.01528 0.00906 -0.0127 0.0320 0.9952 8.750 1.0739 0.01590 0.00969 -0.0141 0.0281 0.9959 9.000 1.1001 0.01665 0.01044 -0.0155 0.0239 0.9968 9.250 1.1250 0.01738 0.01119 -0.0166 0.0211 0.9979 9.500 1.1485 0.01821 0.01202 -0.0175 0.0183 0.9990 9.750 1.1666 0.01895 0.01279 -0.0173 0.0171 1.0000 10.000 1.1613 0.01964 0.01351 -0.0123 0.0163 1.0000 10.250 1.1627 0.02037 0.01424 -0.0088 0.0152 1.0000 10.500 1.1677 0.02115 0.01504 -0.0060 0.0139 1.0000 10.750 1.1778 0.02187 0.01580 -0.0042 0.0131 1.0000 11.000 1.1903 0.02266 0.01662 -0.0029 0.0123 1.0000 11.250 1.2034 0.02350 0.01749 -0.0018 0.0115 1.0000 11.500 1.2162 0.02443 0.01844 -0.0009 0.0107 1.0000 11.750 1.2289 0.02541 0.01945 0.0001 0.0099 1.0000 12.000 1.2431 0.02629 0.02038 0.0008 0.0095 1.0000 12.250 1.2566 0.02726 0.02139 0.0015 0.0090 1.0000 12.500 1.2696 0.02826 0.02244 0.0022 0.0085 1.0000 12.750 1.2818 0.02933 0.02354 0.0030 0.0080 1.0000 13.000 1.2929 0.03051 0.02477 0.0038 0.0076 1.0000 13.250 1.3033 0.03175 0.02606 0.0046 0.0072 1.0000 13.500 1.3148 0.03292 0.02729 0.0053 0.0070 1.0000 13.750 1.3256 0.03415 0.02858 0.0060 0.0068 1.0000 14.000 1.3361 0.03542 0.02992 0.0067 0.0065 1.0000 14.250 1.3454 0.03680 0.03137 0.0073 0.0063 1.0000 14.500 1.3548 0.03824 0.03287 0.0079 0.0061 1.0000 14.750 1.3636 0.03978 0.03448 0.0085 0.0059 1.0000 15.000 1.3715 0.04143 0.03619 0.0090 0.0057 1.0000 15.250 1.3785 0.04319 0.03801 0.0095 0.0054 1.0000 15.500 1.3832 0.04522 0.04011 0.0099 0.0052 1.0000 15.750 1.3870 0.04741 0.04239 0.0104 0.0050 1.0000 16.000 1.3937 0.04932 0.04438 0.0106 0.0049 1.0000 16.250 1.3992 0.05141 0.04656 0.0108 0.0048 1.0000 16.500 1.4038 0.05363 0.04887 0.0109 0.0047 1.0000 16.750 1.4071 0.05608 0.05140 0.0109 0.0045 1.0000 17.000 1.4096 0.05864 0.05407 0.0109 0.0044 1.0000 17.250 1.4106 0.06143 0.05695 0.0107 0.0043 1.0000 17.500 1.4107 0.06441 0.06003 0.0104 0.0042 1.0000 17.750 1.4098 0.06761 0.06334 0.0100 0.0041 1.0000 18.000 1.4075 0.07106 0.06689 0.0094 0.0040 1.0000 18.250 1.4039 0.07475 0.07068 0.0087 0.0040 1.0000 18.500 1.3988 0.07877 0.07480 0.0077 0.0039 1.0000 18.750 1.3921 0.08314 0.07928 0.0064 0.0038 1.0000 19.000 1.3836 0.08790 0.08416 0.0049 0.0038 1.0000 19.250 1.3732 0.09305 0.08942 0.0032 0.0037 1.0000