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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4285 0.08883 0.08512 -0.0046 0.7218 0.0187 -8.750 -0.4355 0.08356 0.07986 -0.0070 0.7210 0.0189 -8.500 -0.4441 0.07810 0.07442 -0.0098 0.7202 0.0188 -8.250 -0.4573 0.07201 0.06833 -0.0141 0.7195 0.0185 -8.000 -0.4745 0.06592 0.06220 -0.0177 0.7187 0.0180 -7.500 -0.5850 0.05968 0.05524 -0.0122 0.7189 0.0158 -7.250 -0.5707 0.05959 0.05514 -0.0120 0.7180 0.0166 -7.000 -0.5619 0.05601 0.05137 -0.0117 0.7171 0.0171 -6.500 -0.5558 0.04096 0.03515 -0.0076 0.7156 0.0160 -6.250 -0.5415 0.03701 0.03077 -0.0061 0.7143 0.0160 -6.000 -0.5236 0.03405 0.02743 -0.0051 0.7130 0.0162 -5.750 -0.5032 0.03165 0.02468 -0.0042 0.7117 0.0165 -5.500 -0.4809 0.02961 0.02233 -0.0035 0.7104 0.0169 -5.250 -0.4573 0.02769 0.02005 -0.0029 0.7089 0.0174 -5.000 -0.4323 0.02628 0.01836 -0.0025 0.7076 0.0186 -4.750 -0.4063 0.02485 0.01655 -0.0020 0.7065 0.0199 -4.500 -0.3796 0.02346 0.01485 -0.0016 0.7055 0.0204 -4.250 -0.3530 0.02205 0.01326 -0.0013 0.7046 0.0210 -4.000 -0.3266 0.02105 0.01217 -0.0012 0.7037 0.0219 -3.750 -0.2999 0.02030 0.01135 -0.0010 0.7029 0.0230 -3.500 -0.2733 0.01964 0.01061 -0.0008 0.7021 0.0246 -3.250 -0.2465 0.01919 0.01005 -0.0007 0.7014 0.0269 -3.000 -0.2195 0.01849 0.00937 -0.0009 0.6996 0.0293 -2.750 -0.1921 0.01805 0.00894 -0.0011 0.6979 0.0318 -2.500 -0.1645 0.01774 0.00857 -0.0012 0.6964 0.0354 -2.250 -0.1377 0.01735 0.00820 -0.0013 0.6951 0.0411 -2.000 -0.1103 0.01709 0.00788 -0.0014 0.6938 0.0478 -1.750 -0.0834 0.01678 0.00762 -0.0014 0.6926 0.0628 -1.500 -0.0573 0.01637 0.00740 -0.0013 0.6914 0.1058 -1.250 -0.0355 0.01546 0.00719 -0.0008 0.6902 0.2872 -1.000 0.0247 0.01381 0.00781 -0.0064 0.6896 0.9043 -0.750 0.0639 0.01444 0.00833 -0.0079 0.6889 0.9563 -0.500 0.1791 0.01497 0.00866 -0.0255 0.6888 0.9964 -0.250 0.2173 0.01495 0.00854 -0.0281 0.6881 1.0000 0.000 0.2433 0.01495 0.00846 -0.0280 0.6872 1.0000 0.250 0.2713 0.01506 0.00854 -0.0286 0.6854 1.0000 0.500 0.3003 0.01524 0.00870 -0.0295 0.6832 1.0000 0.750 0.3283 0.01538 0.00883 -0.0301 0.6813 1.0000 1.000 0.3556 0.01549 0.00891 -0.0305 0.6794 1.0000 1.250 0.3825 0.01558 0.00899 -0.0307 0.6777 1.0000 1.500 0.4089 0.01564 0.00904 -0.0308 0.6762 1.0000 1.750 0.4350 0.01568 0.00905 -0.0307 0.6749 1.0000 2.000 0.4607 0.01570 0.00906 -0.0304 0.6736 1.0000 2.250 0.4859 0.01567 0.00902 -0.0300 0.6724 1.0000 2.500 0.5149 0.01600 0.00943 -0.0312 0.6677 1.0000 2.750 0.5412 0.01606 0.00952 -0.0312 0.6642 1.0000 3.000 0.5664 0.01600 0.00947 -0.0308 0.6617 1.0000 3.250 0.5912 0.01589 0.00938 -0.0301 0.6597 1.0000 3.500 0.6157 0.01575 0.00924 -0.0293 0.6581 1.0000 3.750 0.6439 0.01609 0.00971 -0.0303 0.6522 1.0000 4.000 0.6681 0.01570 0.00935 -0.0293 0.6471 1.0000 4.250 0.6920 0.01513 0.00879 -0.0279 0.6402 1.0000 4.500 0.7170 0.01471 0.00840 -0.0271 0.6322 1.0000 4.750 0.7426 0.01452 0.00828 -0.0267 0.6257 1.0000 5.000 0.7684 0.01432 0.00817 -0.0263 0.6180 1.0000 5.250 0.7948 0.01425 0.00822 -0.0263 0.6084 1.0000 5.500 0.8208 0.01409 0.00815 -0.0260 0.5972 1.0000 5.750 0.8473 0.01404 0.00821 -0.0260 0.5807 1.0000 6.000 0.8730 0.01382 0.00806 -0.0255 0.5567 1.0000 6.250 0.8961 0.01319 0.00720 -0.0237 0.5045 1.0000 6.500 0.9164 0.01384 0.00714 -0.0229 0.4026 1.0000 6.750 0.9349 0.01536 0.00820 -0.0232 0.3150 1.0000 7.000 0.9503 0.01683 0.00931 -0.0230 0.2480 1.0000 7.250 0.9635 0.01811 0.01036 -0.0222 0.2015 1.0000 7.500 0.9752 0.01925 0.01134 -0.0210 0.1692 1.0000 7.750 0.9852 0.02037 0.01234 -0.0195 0.1437 1.0000 8.000 0.9929 0.02146 0.01335 -0.0177 0.1240 1.0000 8.250 0.9981 0.02249 0.01435 -0.0153 0.1087 1.0000 8.500 0.9975 0.02343 0.01524 -0.0116 0.0976 1.0000 8.750 0.9984 0.02438 0.01615 -0.0083 0.0872 1.0000 9.000 1.0031 0.02531 0.01706 -0.0056 0.0773 1.0000 9.250 1.0099 0.02627 0.01801 -0.0034 0.0685 1.0000 9.500 1.0172 0.02731 0.01904 -0.0014 0.0607 1.0000 9.750 1.0259 0.02836 0.02009 0.0003 0.0538 1.0000 10.000 1.0350 0.02945 0.02123 0.0019 0.0483 1.0000 10.250 1.0445 0.03058 0.02237 0.0033 0.0432 1.0000 10.500 1.0533 0.03181 0.02364 0.0047 0.0394 1.0000 10.750 1.0636 0.03297 0.02487 0.0059 0.0359 1.0000 11.000 1.0715 0.03435 0.02625 0.0071 0.0328 1.0000 11.250 1.0805 0.03568 0.02767 0.0083 0.0304 1.0000 11.500 1.0898 0.03701 0.02912 0.0094 0.0283 1.0000 11.750 1.0982 0.03846 0.03064 0.0105 0.0266 1.0000 12.000 1.1037 0.04016 0.03238 0.0116 0.0250 1.0000 12.250 1.1108 0.04179 0.03410 0.0127 0.0237 1.0000 12.500 1.1194 0.04331 0.03575 0.0136 0.0223 1.0000 12.750 1.1271 0.04492 0.03746 0.0145 0.0209 1.0000 13.000 1.1336 0.04667 0.03931 0.0153 0.0199 1.0000 13.250 1.1383 0.04865 0.04136 0.0160 0.0191 1.0000 13.500 1.1403 0.05096 0.04373 0.0170 0.0184 1.0000 13.750 1.1464 0.05295 0.04590 0.0177 0.0178 1.0000 14.000 1.1518 0.05507 0.04819 0.0183 0.0172 1.0000 14.250 1.1559 0.05736 0.05064 0.0188 0.0164 1.0000 14.500 1.1591 0.05978 0.05320 0.0191 0.0157 1.0000 14.750 1.1613 0.06238 0.05593 0.0192 0.0151 1.0000 15.000 1.1623 0.06519 0.05885 0.0191 0.0146 1.0000 15.250 1.1618 0.06823 0.06200 0.0189 0.0142 1.0000 15.500 1.1596 0.07156 0.06544 0.0187 0.0139 1.0000 15.750 1.1551 0.07530 0.06931 0.0185 0.0136 1.0000 16.000 1.1505 0.07929 0.07353 0.0178 0.0134 1.0000 16.250 1.1438 0.08369 0.07815 0.0168 0.0132 1.0000 16.500 1.1353 0.08858 0.08325 0.0154 0.0130 1.0000 16.750 1.1247 0.09400 0.08889 0.0135 0.0129 1.0000 17.000 1.1124 0.09995 0.09505 0.0112 0.0127 1.0000 17.250 1.0981 0.10652 0.10184 0.0082 0.0126 1.0000 17.500 1.0820 0.11377 0.10930 0.0046 0.0126 1.0000 17.750 1.0641 0.12181 0.11754 0.0004 0.0125 1.0000 18.000 1.0438 0.13082 0.12674 -0.0047 0.0126 1.0000 18.250 1.0203 0.14117 0.13727 -0.0107 0.0127 1.0000 18.500 0.9916 0.15380 0.15008 -0.0181 0.0129 1.0000