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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3777 0.09915 0.09460 -0.0143 0.7693 0.0552 -9.000 -0.3794 0.09468 0.09014 -0.0163 0.7681 0.0547 -8.750 -0.3994 0.08482 0.08028 -0.0226 0.7674 0.0348 -8.500 -0.4007 0.08039 0.07586 -0.0241 0.7663 0.0338 -8.250 -0.4084 0.07496 0.07043 -0.0277 0.7652 0.0328 -8.000 -0.5144 0.08087 0.07606 -0.0219 0.7666 0.0339 -7.750 -0.5145 0.07645 0.07157 -0.0233 0.7651 0.0325 -7.250 -0.5211 0.06243 0.05678 -0.0259 0.7626 0.0271 -7.000 -0.5138 0.05859 0.05273 -0.0255 0.7615 0.0268 -6.750 -0.5049 0.05479 0.04866 -0.0248 0.7604 0.0266 -6.500 -0.4944 0.05108 0.04462 -0.0238 0.7594 0.0265 -6.250 -0.4801 0.04726 0.04028 -0.0230 0.7579 0.0270 -6.000 -0.4649 0.04395 0.03661 -0.0225 0.7560 0.0280 -5.750 -0.4447 0.04209 0.03461 -0.0225 0.7542 0.0292 -5.500 -0.4250 0.03934 0.03144 -0.0217 0.7525 0.0295 -5.250 -0.4036 0.03675 0.02838 -0.0208 0.7510 0.0296 -5.000 -0.3805 0.03456 0.02577 -0.0201 0.7497 0.0300 -4.750 -0.3559 0.03267 0.02350 -0.0196 0.7485 0.0307 -4.500 -0.3301 0.03104 0.02152 -0.0192 0.7474 0.0317 -4.250 -0.3037 0.02984 0.01997 -0.0188 0.7463 0.0343 -4.000 -0.2769 0.02870 0.01852 -0.0183 0.7451 0.0362 -3.750 -0.2480 0.02731 0.01709 -0.0191 0.7432 0.0380 -3.500 -0.2195 0.02640 0.01615 -0.0197 0.7413 0.0403 -3.250 -0.1917 0.02581 0.01545 -0.0200 0.7397 0.0449 -3.000 -0.1657 0.02506 0.01467 -0.0201 0.7382 0.0490 -2.750 -0.1405 0.02451 0.01410 -0.0199 0.7366 0.0540 -2.500 -0.1156 0.02405 0.01359 -0.0196 0.7349 0.0629 -2.250 -0.0907 0.02363 0.01310 -0.0191 0.7334 0.0749 -2.000 -0.0660 0.02309 0.01274 -0.0187 0.7321 0.1100 -1.750 0.0205 0.02070 0.01338 -0.0288 0.7322 0.9002 -1.500 0.1435 0.02141 0.01367 -0.0466 0.7325 1.0000 -1.250 0.1683 0.02151 0.01358 -0.0465 0.7313 1.0000 -1.000 0.1945 0.02168 0.01361 -0.0469 0.7296 1.0000 -0.750 0.2233 0.02196 0.01380 -0.0483 0.7269 1.0000 -0.500 0.2505 0.02224 0.01397 -0.0491 0.7248 1.0000 -0.250 0.2764 0.02248 0.01413 -0.0495 0.7226 1.0000 0.000 0.3012 0.02270 0.01426 -0.0495 0.7205 1.0000 0.250 0.3255 0.02292 0.01441 -0.0493 0.7188 1.0000 0.500 0.3491 0.02311 0.01453 -0.0488 0.7172 1.0000 0.750 0.3731 0.02337 0.01474 -0.0486 0.7154 1.0000 1.000 0.4002 0.02395 0.01533 -0.0500 0.7114 1.0000 1.250 0.4245 0.02432 0.01569 -0.0502 0.7082 1.0000 1.500 0.4478 0.02461 0.01596 -0.0498 0.7055 1.0000 1.750 0.4705 0.02480 0.01613 -0.0490 0.7033 1.0000 2.000 0.4928 0.02494 0.01625 -0.0479 0.7016 1.0000 2.250 0.5168 0.02572 0.01711 -0.0491 0.6953 1.0000 2.500 0.5391 0.02601 0.01741 -0.0485 0.6915 1.0000 2.750 0.5614 0.02613 0.01755 -0.0474 0.6888 1.0000 3.000 0.5839 0.02615 0.01758 -0.0460 0.6868 1.0000 3.250 0.6044 0.02704 0.01859 -0.0467 0.6787 1.0000 3.500 0.6266 0.02715 0.01874 -0.0456 0.6752 1.0000 3.750 0.6495 0.02707 0.01870 -0.0442 0.6728 1.0000 4.000 0.6679 0.02789 0.01962 -0.0441 0.6642 1.0000 4.250 0.6908 0.02779 0.01961 -0.0428 0.6603 1.0000 4.750 0.7346 0.02741 0.01938 -0.0400 0.6461 1.0000 5.000 0.7554 0.02716 0.01923 -0.0386 0.6354 1.0000 5.250 0.7821 0.02596 0.01812 -0.0364 0.6300 1.0000 5.500 0.8018 0.02602 0.01832 -0.0354 0.6179 1.0000 5.750 0.8217 0.02598 0.01841 -0.0343 0.6060 1.0000 6.000 0.8418 0.02586 0.01846 -0.0331 0.5931 1.0000 6.250 0.8605 0.02584 0.01859 -0.0319 0.5779 1.0000 6.750 0.8888 0.02650 0.01952 -0.0291 0.5338 1.0000 7.000 0.9099 0.02590 0.01898 -0.0272 0.5021 1.0000 7.250 0.9553 0.02212 0.01480 -0.0237 0.4299 1.0000 7.500 0.9636 0.02262 0.01471 -0.0202 0.3521 1.0000 7.750 0.9628 0.02413 0.01585 -0.0172 0.2936 1.0000 8.000 0.9596 0.02565 0.01706 -0.0139 0.2484 1.0000 8.250 0.9547 0.02693 0.01810 -0.0098 0.2153 1.0000 8.500 0.9541 0.02814 0.01913 -0.0065 0.1867 1.0000 8.750 0.9572 0.02932 0.02019 -0.0038 0.1613 1.0000 9.000 0.9621 0.03053 0.02127 -0.0014 0.1402 1.0000 9.250 0.9692 0.03170 0.02237 0.0006 0.1217 1.0000 9.500 0.9764 0.03293 0.02354 0.0024 0.1059 1.0000 9.750 0.9843 0.03418 0.02477 0.0041 0.0932 1.0000 10.000 0.9922 0.03549 0.02605 0.0057 0.0826 1.0000 10.250 0.9990 0.03693 0.02746 0.0073 0.0744 1.0000 10.500 1.0085 0.03823 0.02885 0.0087 0.0667 1.0000 10.750 1.0158 0.03973 0.03035 0.0102 0.0607 1.0000 11.000 1.0251 0.04113 0.03185 0.0115 0.0552 1.0000 11.250 1.0311 0.04284 0.03350 0.0128 0.0512 1.0000 11.500 1.0420 0.04423 0.03508 0.0140 0.0469 1.0000 11.750 1.0504 0.04582 0.03674 0.0151 0.0434 1.0000 12.000 1.0575 0.04764 0.03856 0.0163 0.0410 1.0000 12.250 1.0689 0.04922 0.04037 0.0175 0.0383 1.0000 12.500 1.0775 0.05098 0.04228 0.0184 0.0357 1.0000 12.750 1.0840 0.05287 0.04425 0.0193 0.0337 1.0000 13.000 1.0916 0.05494 0.04634 0.0203 0.0322 1.0000 13.250 1.1005 0.05713 0.04879 0.0213 0.0310 1.0000 13.500 1.1061 0.05963 0.05156 0.0222 0.0297 1.0000 13.750 1.1083 0.06232 0.05450 0.0229 0.0284 1.0000 14.000 1.1079 0.06513 0.05750 0.0234 0.0272 1.0000 14.250 1.1065 0.06800 0.06052 0.0236 0.0263 1.0000 14.500 1.1043 0.07099 0.06365 0.0237 0.0255 1.0000 14.750 1.1014 0.07436 0.06714 0.0238 0.0248 1.0000 15.000 1.0942 0.07853 0.07150 0.0236 0.0244 1.0000 15.250 1.0819 0.08340 0.07667 0.0228 0.0242 1.0000 15.500 1.0671 0.08888 0.08243 0.0214 0.0240 1.0000 15.750 1.0502 0.09500 0.08882 0.0193 0.0239 1.0000 16.000 1.0312 0.10187 0.09593 0.0163 0.0239 1.0000 16.250 1.0107 0.10957 0.10385 0.0125 0.0239 1.0000 16.500 0.9885 0.11827 0.11275 0.0077 0.0240 1.0000 16.750 0.9647 0.12813 0.12278 0.0019 0.0241 1.0000 17.000 0.9395 0.13929 0.13404 -0.0049 0.0244 1.0000