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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5618 0.08515 0.08241 0.0006 0.7193 0.0188 -8.000 -0.5710 0.08025 0.07747 -0.0023 0.7185 0.0190 -7.750 -0.5738 0.07451 0.07164 -0.0056 0.7177 0.0195 -7.500 -0.5698 0.06742 0.06432 -0.0088 0.7169 0.0204 -7.250 -0.5651 0.06242 0.05910 -0.0090 0.7161 0.0206 -7.000 -0.5601 0.05764 0.05408 -0.0084 0.7153 0.0206 -6.750 -0.5672 0.05016 0.04643 -0.0074 0.7143 0.0213 -6.500 -0.5534 0.04784 0.04404 -0.0070 0.7131 0.0218 -6.250 -0.5378 0.04560 0.04171 -0.0065 0.7120 0.0223 -6.000 -0.5213 0.04307 0.03903 -0.0059 0.7110 0.0232 -5.750 -0.5037 0.04010 0.03582 -0.0048 0.7100 0.0248 -5.500 -0.4779 0.03919 0.03440 -0.0029 0.7089 0.0272 -5.250 -0.4712 0.03238 0.02715 -0.0009 0.7080 0.0285 -5.000 -0.4486 0.03090 0.02569 -0.0009 0.7070 0.0296 -4.750 -0.4281 0.02462 0.01835 0.0032 0.7062 0.0208 -4.500 -0.4041 0.02165 0.01511 0.0041 0.7053 0.0201 -4.250 -0.3778 0.02017 0.01336 0.0046 0.7045 0.0203 -4.000 -0.3506 0.01930 0.01229 0.0049 0.7035 0.0206 -3.750 -0.3247 0.01728 0.01010 0.0053 0.7027 0.0213 -3.500 -0.2982 0.01655 0.00936 0.0054 0.7019 0.0227 -3.250 -0.2707 0.01601 0.00879 0.0054 0.7010 0.0239 -3.000 -0.2431 0.01542 0.00816 0.0054 0.7000 0.0251 -2.750 -0.2152 0.01499 0.00770 0.0053 0.6989 0.0266 -2.500 -0.1889 0.01432 0.00700 0.0056 0.6977 0.0288 -2.250 -0.1614 0.01398 0.00668 0.0055 0.6964 0.0323 -2.000 -0.1331 0.01383 0.00651 0.0053 0.6951 0.0359 -1.750 -0.1063 0.01339 0.00607 0.0054 0.6939 0.0434 -1.500 -0.0787 0.01312 0.00584 0.0053 0.6929 0.0567 -1.250 -0.0535 0.01249 0.00563 0.0055 0.6920 0.1611 -1.000 -0.0364 0.01099 0.00543 0.0068 0.6910 0.5144 -0.750 -0.0128 0.00992 0.00584 0.0087 0.6901 0.9271 -0.500 0.0197 0.01033 0.00618 0.0084 0.6892 0.9549 -0.250 0.0795 0.01085 0.00660 0.0019 0.6886 0.9692 0.000 0.1780 0.01149 0.00714 -0.0127 0.6883 0.9883 0.250 0.2550 0.01157 0.00714 -0.0232 0.6879 1.0000 0.500 0.2815 0.01163 0.00715 -0.0232 0.6869 1.0000 0.750 0.3098 0.01168 0.00722 -0.0238 0.6853 1.0000 1.000 0.3382 0.01176 0.00731 -0.0244 0.6835 1.0000 1.250 0.3658 0.01181 0.00736 -0.0248 0.6816 1.0000 1.500 0.3927 0.01180 0.00735 -0.0249 0.6796 1.0000 1.750 0.4184 0.01168 0.00721 -0.0246 0.6776 1.0000 2.000 0.4436 0.01152 0.00701 -0.0241 0.6755 1.0000 2.250 0.4688 0.01139 0.00685 -0.0236 0.6739 1.0000 2.500 0.4946 0.01135 0.00678 -0.0233 0.6725 1.0000 2.750 0.5230 0.01142 0.00690 -0.0238 0.6696 1.0000 3.000 0.5502 0.01137 0.00689 -0.0240 0.6663 1.0000 3.250 0.5743 0.01095 0.00644 -0.0229 0.6621 1.0000 3.500 0.5970 0.01045 0.00583 -0.0214 0.6582 1.0000 3.750 0.6243 0.01030 0.00575 -0.0215 0.6526 1.0000 4.000 0.6504 0.01009 0.00556 -0.0211 0.6486 1.0000 4.250 0.6758 0.00984 0.00530 -0.0205 0.6453 1.0000 4.500 0.7023 0.00970 0.00519 -0.0204 0.6411 1.0000 4.750 0.7292 0.00954 0.00509 -0.0203 0.6353 1.0000 5.000 0.7547 0.00926 0.00480 -0.0197 0.6303 1.0000 5.250 0.7821 0.00915 0.00479 -0.0198 0.6231 1.0000 5.500 0.8080 0.00890 0.00453 -0.0193 0.6154 1.0000 5.750 0.8352 0.00876 0.00447 -0.0193 0.6029 1.0000 6.000 0.8623 0.00864 0.00442 -0.0193 0.5856 1.0000 6.250 0.8894 0.00858 0.00434 -0.0193 0.5522 1.0000 6.500 0.9188 0.00959 0.00471 -0.0210 0.4288 1.0000 6.750 0.9465 0.01127 0.00582 -0.0234 0.3145 1.0000 7.000 0.9700 0.01263 0.00676 -0.0245 0.2333 1.0000 7.250 0.9914 0.01373 0.00758 -0.0249 0.1813 1.0000 7.500 1.0113 0.01465 0.00832 -0.0249 0.1449 1.0000 7.750 1.0299 0.01550 0.00904 -0.0244 0.1183 1.0000 8.000 1.0468 0.01634 0.00979 -0.0237 0.0972 1.0000 8.250 1.0619 0.01722 0.01059 -0.0228 0.0803 1.0000 8.500 1.0746 0.01820 0.01152 -0.0217 0.0674 1.0000 8.750 1.0837 0.01918 0.01247 -0.0200 0.0581 1.0000 9.000 1.0840 0.02025 0.01350 -0.0166 0.0511 1.0000 9.250 1.0817 0.02098 0.01429 -0.0123 0.0474 1.0000 9.500 1.0801 0.02194 0.01522 -0.0085 0.0429 1.0000 9.750 1.0839 0.02286 0.01617 -0.0056 0.0392 1.0000 10.000 1.0911 0.02376 0.01709 -0.0034 0.0356 1.0000 10.250 1.0943 0.02511 0.01844 -0.0010 0.0318 1.0000 10.500 1.1071 0.02595 0.01934 0.0002 0.0296 1.0000 10.750 1.1179 0.02699 0.02041 0.0015 0.0273 1.0000 11.000 1.1215 0.02862 0.02206 0.0033 0.0250 1.0000 11.250 1.1313 0.02983 0.02336 0.0045 0.0237 1.0000 11.500 1.1430 0.03093 0.02453 0.0055 0.0223 1.0000 11.750 1.1540 0.03211 0.02575 0.0064 0.0209 1.0000 12.000 1.1626 0.03348 0.02716 0.0075 0.0196 1.0000 12.250 1.1605 0.03576 0.02951 0.0095 0.0184 1.0000 12.500 1.1718 0.03699 0.03082 0.0103 0.0179 1.0000 12.750 1.1815 0.03837 0.03230 0.0111 0.0172 1.0000 13.000 1.1899 0.03988 0.03390 0.0121 0.0165 1.0000 13.250 1.1981 0.04142 0.03553 0.0129 0.0158 1.0000 13.500 1.2060 0.04304 0.03721 0.0135 0.0152 1.0000 13.750 1.2120 0.04487 0.03910 0.0142 0.0145 1.0000 14.000 1.2119 0.04732 0.04164 0.0155 0.0139 1.0000 14.250 1.2148 0.04958 0.04403 0.0165 0.0134 1.0000 14.500 1.2209 0.05159 0.04617 0.0169 0.0131 1.0000 14.750 1.2252 0.05384 0.04856 0.0174 0.0128 1.0000 15.000 1.2284 0.05626 0.05110 0.0178 0.0124 1.0000 15.250 1.2302 0.05887 0.05385 0.0180 0.0121 1.0000 15.500 1.2308 0.06171 0.05682 0.0181 0.0118 1.0000 15.750 1.2305 0.06474 0.05999 0.0180 0.0115 1.0000 16.000 1.2292 0.06796 0.06333 0.0177 0.0113 1.0000 16.250 1.2267 0.07142 0.06691 0.0172 0.0110 1.0000 16.500 1.2230 0.07514 0.07075 0.0166 0.0109 1.0000 16.750 1.2180 0.07918 0.07490 0.0157 0.0107 1.0000 17.000 1.2105 0.08364 0.07949 0.0145 0.0105 1.0000 17.250 1.1993 0.08880 0.08480 0.0131 0.0103 1.0000 17.500 1.1845 0.09479 0.09096 0.0112 0.0102 1.0000 17.750 1.1667 0.10154 0.09790 0.0086 0.0101 1.0000 18.000 1.1485 0.10871 0.10526 0.0055 0.0101 1.0000