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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5014 0.09449 0.09117 -0.0083 0.7883 0.0415 -8.250 -0.5030 0.08933 0.08603 -0.0140 0.7872 0.0424 -8.000 -0.5071 0.08446 0.08114 -0.0187 0.7857 0.0432 -7.750 -0.5102 0.07967 0.07627 -0.0227 0.7845 0.0445 -7.500 -0.5142 0.07517 0.07138 -0.0272 0.7833 0.0465 -7.250 -0.5102 0.07222 0.06811 -0.0276 0.7822 0.0469 -7.000 -0.5061 0.06459 0.06063 -0.0286 0.7813 0.0484 -6.750 -0.4908 0.06226 0.05836 -0.0286 0.7802 0.0503 -6.500 -0.4774 0.05950 0.05548 -0.0288 0.7792 0.0531 -6.250 -0.4638 0.05877 0.05397 -0.0276 0.7778 0.0592 -6.000 -0.4569 0.05203 0.04718 -0.0276 0.7766 0.0609 -5.750 -0.4397 0.04920 0.04438 -0.0274 0.7755 0.0627 -5.500 -0.4219 0.04701 0.04206 -0.0269 0.7746 0.0660 -5.250 -0.4074 0.04471 0.03915 -0.0250 0.7738 0.0745 -5.000 -0.3848 0.04197 0.03648 -0.0258 0.7729 0.0774 -4.750 -0.3625 0.04034 0.03439 -0.0258 0.7717 0.0889 -4.500 -0.3374 0.03795 0.03208 -0.0267 0.7702 0.0934 -4.250 -0.3034 0.03251 0.02512 -0.0229 0.7685 0.0471 -4.000 -0.2766 0.02902 0.02142 -0.0231 0.7673 0.0440 -3.750 -0.2477 0.02727 0.01938 -0.0232 0.7662 0.0431 -3.500 -0.2185 0.02602 0.01791 -0.0234 0.7652 0.0436 -3.250 -0.1900 0.02521 0.01692 -0.0235 0.7639 0.0454 -3.000 -0.1635 0.02415 0.01579 -0.0233 0.7625 0.0490 -2.750 -0.1383 0.02344 0.01510 -0.0228 0.7613 0.0525 -2.500 -0.1132 0.02303 0.01466 -0.0224 0.7603 0.0573 -2.250 -0.0902 0.02256 0.01421 -0.0216 0.7595 0.0656 -2.000 -0.0618 0.02228 0.01399 -0.0229 0.7574 0.0788 -1.750 -0.0036 0.01917 0.01425 -0.0285 0.7563 0.8990 -1.500 0.1010 0.02043 0.01520 -0.0419 0.7557 0.9778 -1.250 0.1927 0.02047 0.01502 -0.0551 0.7551 1.0000 -1.000 0.2208 0.02074 0.01520 -0.0563 0.7531 1.0000 -0.750 0.2471 0.02098 0.01536 -0.0569 0.7510 1.0000 -0.500 0.2724 0.02124 0.01553 -0.0571 0.7492 1.0000 -0.250 0.2956 0.02144 0.01566 -0.0566 0.7474 1.0000 0.000 0.3173 0.02163 0.01578 -0.0555 0.7459 1.0000 0.250 0.3452 0.02211 0.01623 -0.0568 0.7431 1.0000 0.500 0.3740 0.02262 0.01674 -0.0587 0.7392 1.0000 0.750 0.3981 0.02292 0.01701 -0.0587 0.7360 1.0000 1.000 0.4200 0.02310 0.01715 -0.0577 0.7334 1.0000 1.250 0.4400 0.02320 0.01721 -0.0557 0.7314 1.0000 1.500 0.4671 0.02394 0.01798 -0.0577 0.7254 1.0000 1.750 0.4898 0.02424 0.01828 -0.0573 0.7213 1.0000 2.000 0.5110 0.02430 0.01833 -0.0557 0.7185 1.0000 2.250 0.5311 0.02429 0.01830 -0.0535 0.7166 1.0000 2.500 0.5556 0.02520 0.01928 -0.0554 0.7083 1.0000 2.750 0.5772 0.02523 0.01931 -0.0539 0.7048 1.0000 3.000 0.5985 0.02508 0.01917 -0.0518 0.7026 1.0000 3.250 0.6200 0.02586 0.02002 -0.0524 0.6941 1.0000 3.500 0.6422 0.02566 0.01984 -0.0507 0.6902 1.0000 3.750 0.6644 0.02491 0.01907 -0.0477 0.6877 1.0000 4.000 0.6863 0.02478 0.01902 -0.0468 0.6769 1.0000 4.250 0.7090 0.02346 0.01768 -0.0432 0.6737 1.0000 4.500 0.7316 0.02342 0.01772 -0.0425 0.6644 1.0000 4.750 0.7550 0.02249 0.01681 -0.0400 0.6607 1.0000 5.000 0.7782 0.02135 0.01569 -0.0372 0.6585 1.0000 5.250 0.8020 0.02128 0.01574 -0.0368 0.6485 1.0000 5.500 0.8260 0.02002 0.01450 -0.0341 0.6453 1.0000 5.750 0.8502 0.01948 0.01406 -0.0330 0.6362 1.0000 6.000 0.8747 0.01814 0.01277 -0.0305 0.6313 1.0000 6.250 0.8997 0.01739 0.01214 -0.0294 0.6205 1.0000 6.500 0.9249 0.01640 0.01125 -0.0279 0.6085 1.0000 6.750 0.9506 0.01555 0.01053 -0.0267 0.5905 1.0000 7.000 0.9765 0.01498 0.01006 -0.0260 0.5580 1.0000 7.250 0.9982 0.01386 0.00847 -0.0230 0.4736 1.0000 7.500 1.0104 0.01559 0.00930 -0.0221 0.3446 1.0000 7.750 1.0163 0.01778 0.01093 -0.0211 0.2532 1.0000 8.000 1.0187 0.01964 0.01245 -0.0192 0.1995 1.0000 8.250 1.0191 0.02129 0.01390 -0.0169 0.1655 1.0000 8.500 1.0146 0.02272 0.01518 -0.0133 0.1436 1.0000 8.750 1.0068 0.02399 0.01632 -0.0087 0.1280 1.0000 9.000 1.0051 0.02523 0.01747 -0.0052 0.1123 1.0000 9.250 1.0065 0.02652 0.01868 -0.0024 0.0983 1.0000 9.500 1.0092 0.02790 0.01997 0.0001 0.0867 1.0000 9.750 1.0155 0.02916 0.02121 0.0021 0.0768 1.0000 10.000 1.0235 0.03040 0.02249 0.0039 0.0684 1.0000 10.250 1.0292 0.03189 0.02391 0.0059 0.0620 1.0000 10.500 1.0405 0.03301 0.02512 0.0073 0.0563 1.0000 10.750 1.0487 0.03452 0.02653 0.0092 0.0512 1.0000 11.000 1.0615 0.03563 0.02780 0.0104 0.0474 1.0000 11.250 1.0736 0.03687 0.02906 0.0117 0.0440 1.0000 11.500 1.0909 0.03834 0.03049 0.0135 0.0406 1.0000 11.750 1.1038 0.03959 0.03195 0.0146 0.0383 1.0000 12.000 1.1162 0.04096 0.03343 0.0157 0.0359 1.0000 12.250 1.1301 0.04241 0.03493 0.0167 0.0340 1.0000 12.500 1.1555 0.04496 0.03759 0.0181 0.0319 1.0000 12.750 1.1617 0.04685 0.03974 0.0193 0.0311 1.0000 13.000 1.1666 0.04900 0.04214 0.0205 0.0300 1.0000 13.250 1.1700 0.05130 0.04467 0.0217 0.0288 1.0000 13.500 1.1723 0.05376 0.04733 0.0227 0.0279 1.0000 13.750 1.1728 0.05655 0.05034 0.0237 0.0272 1.0000 14.000 1.1695 0.05967 0.05367 0.0246 0.0268 1.0000 14.250 1.1636 0.06306 0.05728 0.0253 0.0264 1.0000 14.500 1.1548 0.06680 0.06124 0.0259 0.0261 1.0000 14.750 1.1427 0.07098 0.06564 0.0262 0.0260 1.0000 15.000 1.1266 0.07569 0.07059 0.0260 0.0260 1.0000 15.250 1.1066 0.08110 0.07626 0.0253 0.0260 1.0000 15.500 1.0821 0.08754 0.08297 0.0237 0.0262 1.0000 15.750 1.0391 0.09771 0.09351 0.0195 0.0270 1.0000 16.000 0.9945 0.10989 0.10598 0.0130 0.0278 1.0000 16.250 0.9478 0.12488 0.12120 0.0037 0.0290 1.0000 16.500 0.8984 0.14373 0.14014 -0.0075 0.0307 1.0000 16.750 0.8756 0.15595 0.15233 -0.0134 0.0317 1.0000