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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4726 0.08595 0.08368 0.0028 0.6909 0.0119 -9.000 -0.4792 0.08096 0.07869 0.0009 0.6903 0.0120 -8.750 -0.4885 0.07556 0.07330 -0.0017 0.6898 0.0120 -8.500 -0.5157 0.06665 0.06439 -0.0093 0.6893 0.0119 -8.250 -0.5399 0.06009 0.05778 -0.0117 0.6887 0.0119 -8.000 -0.5574 0.05480 0.05240 -0.0112 0.6878 0.0119 -7.750 -0.5630 0.05013 0.04764 -0.0109 0.6868 0.0120 -7.500 -0.5643 0.04561 0.04301 -0.0102 0.6863 0.0121 -7.250 -0.5617 0.04134 0.03864 -0.0095 0.6857 0.0123 -7.000 -0.5562 0.03725 0.03442 -0.0085 0.6850 0.0124 -6.750 -0.5472 0.03372 0.03077 -0.0076 0.6842 0.0127 -6.500 -0.5999 0.03241 0.02840 0.0031 0.6850 0.0114 -6.250 -0.5967 0.02516 0.02044 0.0070 0.6843 0.0110 -6.000 -0.5800 0.02131 0.01606 0.0091 0.6834 0.0110 -5.750 -0.5575 0.01916 0.01358 0.0101 0.6824 0.0112 -5.500 -0.5317 0.01821 0.01245 0.0105 0.6814 0.0115 -5.250 -0.5081 0.01614 0.01007 0.0113 0.6805 0.0120 -5.000 -0.4826 0.01501 0.00883 0.0117 0.6796 0.0124 -4.750 -0.4557 0.01444 0.00820 0.0118 0.6788 0.0129 -4.500 -0.4286 0.01392 0.00763 0.0119 0.6779 0.0134 -4.250 -0.4015 0.01339 0.00704 0.0120 0.6771 0.0139 -4.000 -0.3745 0.01287 0.00646 0.0122 0.6763 0.0143 -3.750 -0.3474 0.01240 0.00592 0.0123 0.6756 0.0148 -3.500 -0.3200 0.01203 0.00550 0.0124 0.6748 0.0153 -3.250 -0.2937 0.01145 0.00484 0.0127 0.6739 0.0161 -3.000 -0.2666 0.01109 0.00446 0.0128 0.6728 0.0175 -2.750 -0.2386 0.01088 0.00424 0.0127 0.6718 0.0189 -2.500 -0.2103 0.01066 0.00401 0.0125 0.6712 0.0202 -2.250 -0.1827 0.01028 0.00361 0.0126 0.6705 0.0228 -2.000 -0.1543 0.01011 0.00345 0.0124 0.6697 0.0257 -1.750 -0.1259 0.00991 0.00324 0.0122 0.6689 0.0294 -1.500 -0.0975 0.00975 0.00311 0.0120 0.6680 0.0355 -1.250 -0.0693 0.00953 0.00296 0.0119 0.6671 0.0508 -1.000 -0.0420 0.00917 0.00283 0.0118 0.6660 0.1117 -0.750 -0.0165 0.00855 0.00271 0.0119 0.6651 0.2615 -0.500 0.0056 0.00756 0.00258 0.0125 0.6642 0.5138 -0.250 0.0166 0.00613 0.00260 0.0163 0.6634 0.9084 0.000 0.0425 0.00627 0.00274 0.0171 0.6625 0.9434 0.250 0.0681 0.00643 0.00288 0.0178 0.6616 0.9581 0.500 0.1010 0.00666 0.00308 0.0171 0.6607 0.9677 0.750 0.1769 0.00729 0.00366 0.0070 0.6602 0.9782 1.000 0.2360 0.00765 0.00398 0.0003 0.6595 0.9862 1.250 0.2825 0.00778 0.00407 -0.0039 0.6584 0.9893 1.500 0.3144 0.00776 0.00404 -0.0049 0.6567 0.9905 1.750 0.3456 0.00765 0.00395 -0.0058 0.6542 0.9917 2.000 0.3760 0.00757 0.00386 -0.0065 0.6516 0.9931 2.250 0.4052 0.00753 0.00381 -0.0070 0.6496 0.9943 2.500 0.4379 0.00745 0.00371 -0.0082 0.6478 0.9948 2.750 0.4699 0.00733 0.00354 -0.0092 0.6443 0.9954 3.000 0.5019 0.00716 0.00340 -0.0102 0.6390 0.9961 3.250 0.5336 0.00703 0.00327 -0.0112 0.6347 0.9968 3.500 0.5654 0.00694 0.00318 -0.0122 0.6314 0.9976 3.750 0.5970 0.00689 0.00314 -0.0132 0.6277 0.9983 4.000 0.6284 0.00682 0.00311 -0.0142 0.6235 0.9990 4.250 0.6596 0.00674 0.00305 -0.0151 0.6186 0.9997 4.500 0.6894 0.00669 0.00301 -0.0157 0.6127 1.0000 4.750 0.7168 0.00663 0.00300 -0.0158 0.6062 1.0000 5.000 0.7442 0.00659 0.00298 -0.0160 0.5973 1.0000 5.250 0.7718 0.00656 0.00295 -0.0161 0.5825 1.0000 5.500 0.8000 0.00662 0.00294 -0.0165 0.5515 1.0000 5.750 0.8328 0.00737 0.00328 -0.0186 0.4553 1.0000 6.000 0.8662 0.00856 0.00398 -0.0214 0.3473 1.0000 6.250 0.8964 0.00962 0.00461 -0.0235 0.2592 1.0000 6.500 0.9241 0.01041 0.00513 -0.0247 0.2031 1.0000 6.750 0.9504 0.01110 0.00562 -0.0255 0.1613 1.0000 7.000 0.9756 0.01170 0.00606 -0.0260 0.1318 1.0000 7.250 0.9999 0.01227 0.00652 -0.0262 0.1074 1.0000 7.500 1.0231 0.01286 0.00699 -0.0263 0.0872 1.0000 7.750 1.0457 0.01338 0.00746 -0.0262 0.0728 1.0000 8.000 1.0673 0.01393 0.00795 -0.0259 0.0607 1.0000 8.250 1.0878 0.01451 0.00849 -0.0255 0.0505 1.0000 8.500 1.1068 0.01514 0.00907 -0.0249 0.0420 1.0000 8.750 1.1253 0.01571 0.00964 -0.0241 0.0366 1.0000 9.000 1.1415 0.01645 0.01039 -0.0233 0.0313 1.0000 9.250 1.1562 0.01721 0.01116 -0.0223 0.0281 1.0000 9.500 1.1634 0.01824 0.01219 -0.0203 0.0245 1.0000 9.750 1.1681 0.01892 0.01292 -0.0173 0.0234 1.0000 10.000 1.1625 0.01962 0.01364 -0.0123 0.0223 1.0000 10.250 1.1628 0.02038 0.01441 -0.0086 0.0207 1.0000 10.500 1.1630 0.02143 0.01547 -0.0052 0.0185 1.0000 10.750 1.1741 0.02214 0.01623 -0.0035 0.0177 1.0000 11.000 1.1866 0.02295 0.01708 -0.0023 0.0166 1.0000 11.250 1.1988 0.02387 0.01802 -0.0012 0.0155 1.0000 11.500 1.2079 0.02509 0.01928 0.0001 0.0142 1.0000 11.750 1.2174 0.02632 0.02057 0.0013 0.0134 1.0000 12.000 1.2317 0.02723 0.02153 0.0020 0.0129 1.0000 12.250 1.2449 0.02822 0.02257 0.0028 0.0122 1.0000 12.500 1.2578 0.02924 0.02364 0.0035 0.0116 1.0000 12.750 1.2683 0.03047 0.02490 0.0043 0.0111 1.0000 13.000 1.2747 0.03205 0.02654 0.0054 0.0104 1.0000 13.250 1.2762 0.03404 0.02863 0.0068 0.0099 1.0000 13.500 1.2880 0.03522 0.02987 0.0074 0.0097 1.0000 13.750 1.2979 0.03656 0.03129 0.0081 0.0094 1.0000 14.000 1.3068 0.03803 0.03282 0.0088 0.0091 1.0000 14.250 1.3155 0.03958 0.03444 0.0094 0.0088 1.0000 14.500 1.3233 0.04125 0.03618 0.0099 0.0085 1.0000 14.750 1.3311 0.04293 0.03794 0.0104 0.0082 1.0000 15.000 1.3369 0.04487 0.03994 0.0108 0.0079 1.0000 15.250 1.3386 0.04727 0.04241 0.0113 0.0076 1.0000 15.500 1.3306 0.05071 0.04598 0.0120 0.0073 1.0000 15.750 1.3301 0.05350 0.04889 0.0123 0.0071 1.0000 16.000 1.3361 0.05568 0.05115 0.0123 0.0070 1.0000 16.250 1.3397 0.05816 0.05373 0.0123 0.0069 1.0000 16.500 1.3408 0.06097 0.05664 0.0122 0.0067 1.0000 16.750 1.3406 0.06403 0.05981 0.0119 0.0066 1.0000 17.000 1.3397 0.06728 0.06316 0.0114 0.0065 1.0000 17.250 1.3368 0.07087 0.06687 0.0108 0.0063 1.0000 17.500 1.3332 0.07462 0.07072 0.0101 0.0062 1.0000 17.750 1.3286 0.07865 0.07486 0.0091 0.0061 1.0000 18.000 1.3222 0.08307 0.07940 0.0078 0.0060 1.0000 18.250 1.3150 0.08774 0.08418 0.0063 0.0059 1.0000 18.500 1.3059 0.09279 0.08935 0.0045 0.0058 1.0000 18.750 1.2955 0.09820 0.09487 0.0025 0.0058 1.0000 19.000 1.2837 0.10399 0.10078 0.0001 0.0057 1.0000 19.250 1.2705 0.11016 0.10706 -0.0026 0.0057 1.0000