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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.6072 0.08278 0.07979 0.0037 0.6878 0.0079 -8.500 -0.6209 0.07697 0.07394 0.0002 0.6870 0.0079 -8.250 -0.6314 0.07035 0.06722 -0.0026 0.6862 0.0079 -8.000 -0.6386 0.06337 0.06010 -0.0042 0.6854 0.0079 -7.750 -0.6461 0.05519 0.05168 -0.0044 0.6845 0.0080 -7.500 -0.6987 0.03129 0.02634 0.0027 0.6840 0.0084 -7.250 -0.6894 0.02659 0.02102 0.0051 0.6830 0.0087 -7.000 -0.6669 0.02559 0.01988 0.0056 0.6820 0.0090 -6.750 -0.6433 0.02470 0.01885 0.0060 0.6810 0.0092 -6.500 -0.6201 0.02347 0.01742 0.0066 0.6800 0.0096 -6.250 -0.5973 0.02178 0.01543 0.0073 0.6791 0.0099 -6.000 -0.5734 0.02020 0.01356 0.0080 0.6782 0.0102 -5.750 -0.5485 0.01892 0.01204 0.0085 0.6773 0.0106 -5.500 -0.5228 0.01788 0.01079 0.0089 0.6764 0.0110 -5.250 -0.4967 0.01703 0.00978 0.0092 0.6756 0.0113 -5.000 -0.4702 0.01636 0.00896 0.0095 0.6748 0.0116 -4.750 -0.4447 0.01546 0.00796 0.0098 0.6740 0.0121 -4.500 -0.4181 0.01496 0.00741 0.0100 0.6731 0.0125 -4.250 -0.3910 0.01461 0.00702 0.0100 0.6723 0.0133 -4.000 -0.3637 0.01423 0.00660 0.0100 0.6713 0.0141 -3.750 -0.3365 0.01380 0.00611 0.0101 0.6705 0.0149 -3.500 -0.3092 0.01341 0.00567 0.0101 0.6695 0.0155 -3.250 -0.2825 0.01291 0.00515 0.0102 0.6686 0.0166 -3.000 -0.2549 0.01261 0.00485 0.0102 0.6677 0.0178 -2.750 -0.2271 0.01236 0.00456 0.0101 0.6667 0.0193 -2.500 -0.1991 0.01213 0.00431 0.0100 0.6658 0.0209 -2.250 -0.1714 0.01187 0.00407 0.0099 0.6648 0.0241 -2.000 -0.1432 0.01169 0.00386 0.0098 0.6638 0.0270 -1.750 -0.1153 0.01146 0.00364 0.0097 0.6628 0.0322 -1.500 -0.0872 0.01128 0.00347 0.0096 0.6619 0.0400 -1.250 -0.0592 0.01109 0.00333 0.0094 0.6611 0.0537 -1.000 -0.0316 0.01083 0.00320 0.0093 0.6603 0.0903 -0.500 0.0200 0.00984 0.00297 0.0094 0.6589 0.3202 -0.250 0.0380 0.00859 0.00279 0.0108 0.6580 0.6191 0.250 0.0993 0.00835 0.00363 0.0112 0.6561 0.9599 0.500 0.1779 0.00898 0.00422 0.0007 0.6554 0.9777 0.750 0.2122 0.00904 0.00425 -0.0008 0.6544 0.9808 1.000 0.2413 0.00906 0.00425 -0.0013 0.6532 0.9825 1.250 0.2697 0.00908 0.00425 -0.0016 0.6519 0.9841 1.500 0.3020 0.00907 0.00423 -0.0028 0.6508 0.9847 1.750 0.3337 0.00907 0.00422 -0.0039 0.6496 0.9854 2.000 0.3653 0.00907 0.00420 -0.0049 0.6484 0.9861 2.250 0.3967 0.00902 0.00413 -0.0058 0.6465 0.9869 2.500 0.4274 0.00893 0.00401 -0.0065 0.6441 0.9878 2.750 0.4583 0.00889 0.00400 -0.0074 0.6406 0.9886 3.000 0.4894 0.00887 0.00401 -0.0083 0.6377 0.9895 3.250 0.5199 0.00882 0.00397 -0.0091 0.6344 0.9905 3.500 0.5493 0.00864 0.00376 -0.0094 0.6287 0.9916 3.750 0.5792 0.00853 0.00369 -0.0100 0.6193 0.9926 4.000 0.6088 0.00846 0.00363 -0.0105 0.6136 0.9936 4.250 0.6392 0.00844 0.00368 -0.0113 0.6063 0.9945 4.500 0.6704 0.00839 0.00365 -0.0122 0.5984 0.9950 4.750 0.7012 0.00835 0.00363 -0.0131 0.5879 0.9956 5.000 0.7320 0.00833 0.00362 -0.0140 0.5685 0.9962 5.250 0.7624 0.00840 0.00358 -0.0148 0.5274 0.9967 5.500 0.7934 0.00934 0.00401 -0.0168 0.4262 0.9968 5.750 0.8240 0.01050 0.00476 -0.0191 0.3379 0.9971 6.000 0.8535 0.01159 0.00549 -0.0211 0.2611 0.9977 6.250 0.8820 0.01246 0.00611 -0.0227 0.2082 0.9983 6.500 0.9099 0.01324 0.00669 -0.0240 0.1681 0.9990 6.750 0.9372 0.01397 0.00728 -0.0252 0.1355 0.9997 7.000 0.9612 0.01463 0.00782 -0.0256 0.1133 1.0000 7.250 0.9824 0.01521 0.00835 -0.0253 0.0966 1.0000 7.500 1.0023 0.01584 0.00892 -0.0248 0.0817 1.0000 7.750 1.0209 0.01648 0.00952 -0.0242 0.0697 1.0000 8.000 1.0380 0.01717 0.01019 -0.0234 0.0595 1.0000 8.250 1.0533 0.01796 0.01095 -0.0225 0.0507 1.0000 8.500 1.0666 0.01875 0.01175 -0.0213 0.0444 1.0000 8.750 1.0761 0.01959 0.01258 -0.0194 0.0394 1.0000 9.000 1.0796 0.02038 0.01338 -0.0163 0.0358 1.0000 9.250 1.0767 0.02115 0.01416 -0.0119 0.0330 1.0000 9.500 1.0806 0.02188 0.01493 -0.0088 0.0307 1.0000 9.750 1.0870 0.02265 0.01572 -0.0063 0.0282 1.0000 10.000 1.0943 0.02352 0.01659 -0.0041 0.0254 1.0000 10.250 1.1048 0.02436 0.01747 -0.0024 0.0234 1.0000 10.500 1.1165 0.02522 0.01837 -0.0011 0.0214 1.0000 10.750 1.1277 0.02620 0.01936 0.0002 0.0195 1.0000 11.000 1.1389 0.02723 0.02044 0.0013 0.0180 1.0000 11.250 1.1515 0.02820 0.02148 0.0023 0.0170 1.0000 11.500 1.1636 0.02924 0.02256 0.0033 0.0159 1.0000 11.750 1.1749 0.03035 0.02371 0.0042 0.0148 1.0000 12.000 1.1838 0.03169 0.02509 0.0053 0.0137 1.0000 12.250 1.1954 0.03282 0.02629 0.0061 0.0131 1.0000 12.500 1.2064 0.03402 0.02757 0.0069 0.0124 1.0000 12.750 1.2164 0.03532 0.02896 0.0077 0.0118 1.0000 13.000 1.2260 0.03667 0.03038 0.0085 0.0113 1.0000 13.250 1.2341 0.03816 0.03193 0.0093 0.0108 1.0000 13.500 1.2403 0.03986 0.03369 0.0102 0.0103 1.0000 13.750 1.2460 0.04168 0.03559 0.0109 0.0099 1.0000 14.000 1.2543 0.04329 0.03731 0.0115 0.0095 1.0000 14.250 1.2616 0.04505 0.03917 0.0120 0.0092 1.0000 14.500 1.2685 0.04690 0.04111 0.0124 0.0088 1.0000 14.750 1.2747 0.04886 0.04316 0.0128 0.0085 1.0000 15.000 1.2801 0.05093 0.04532 0.0131 0.0082 1.0000 15.250 1.2841 0.05322 0.04771 0.0133 0.0079 1.0000 15.500 1.2866 0.05574 0.05032 0.0134 0.0077 1.0000 15.750 1.2866 0.05860 0.05329 0.0134 0.0075 1.0000 16.000 1.2828 0.06199 0.05678 0.0133 0.0072 1.0000 16.250 1.2822 0.06511 0.06003 0.0131 0.0071 1.0000 16.500 1.2815 0.06836 0.06341 0.0127 0.0070 1.0000 16.750 1.2792 0.07187 0.06706 0.0121 0.0069 1.0000 17.000 1.2757 0.07565 0.07097 0.0113 0.0067 1.0000 17.250 1.2707 0.07978 0.07524 0.0103 0.0066 1.0000 17.500 1.2646 0.08420 0.07980 0.0090 0.0065 1.0000 17.750 1.2572 0.08895 0.08468 0.0075 0.0064 1.0000 18.000 1.2483 0.09405 0.08993 0.0056 0.0063 1.0000 18.250 1.2385 0.09947 0.09548 0.0035 0.0062 1.0000 18.500 1.2272 0.10529 0.10145 0.0011 0.0062 1.0000 18.750 1.2149 0.11142 0.10772 -0.0016 0.0061 1.0000 19.000 1.2016 0.11789 0.11433 -0.0046 0.0060 1.0000 19.250 1.1874 0.12472 0.12130 -0.0079 0.0060 1.0000