XFOIL Version 6.96 Calculated polar for: HQ 3.5/18 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9953 0.08099 0.07758 -0.0829 1.0000 0.0177 -19.500 -1.0144 0.07467 0.07114 -0.0865 1.0000 0.0179 -19.250 -1.0317 0.06874 0.06510 -0.0898 1.0000 0.0180 -19.000 -1.0428 0.06383 0.06009 -0.0924 1.0000 0.0183 -18.750 -1.0532 0.05928 0.05544 -0.0948 1.0000 0.0184 -18.500 -1.0581 0.05564 0.05171 -0.0965 1.0000 0.0186 -18.250 -1.0618 0.05228 0.04827 -0.0979 1.0000 0.0189 -18.000 -1.0629 0.04935 0.04527 -0.0990 1.0000 0.0192 -17.750 -1.0635 0.04658 0.04242 -0.1000 1.0000 0.0193 -17.500 -1.0621 0.04411 0.03989 -0.1007 1.0000 0.0195 -17.250 -1.0604 0.04180 0.03750 -0.1012 1.0000 0.0197 -17.000 -1.0596 0.03953 0.03517 -0.1015 1.0000 0.0200 -16.750 -1.0591 0.03730 0.03290 -0.1013 0.9917 0.0203 -16.500 -1.0441 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0.00199 -0.0987 0.6131 0.2226 -1.500 0.3078 0.00781 0.00187 -0.0989 0.6034 0.2926 -1.250 0.3348 0.00769 0.00181 -0.0988 0.5980 0.3227 -1.000 0.3602 0.00720 0.00171 -0.0987 0.5917 0.4457 -0.750 0.3874 0.00720 0.00173 -0.0986 0.5823 0.4687 -0.500 0.4153 0.00721 0.00174 -0.0986 0.5734 0.4827 -0.250 0.4425 0.00727 0.00176 -0.0985 0.5634 0.4927 0.000 0.4699 0.00730 0.00179 -0.0984 0.5524 0.5014 0.250 0.4968 0.00739 0.00183 -0.0982 0.5394 0.5069 0.500 0.5228 0.00749 0.00187 -0.0979 0.5230 0.5132 0.750 0.5478 0.00763 0.00195 -0.0974 0.5036 0.5195 1.000 0.5724 0.00781 0.00204 -0.0968 0.4845 0.5251 1.500 0.6214 0.00816 0.00224 -0.0956 0.4526 0.5328 1.750 0.6464 0.00830 0.00234 -0.0951 0.4425 0.5366 2.000 0.6720 0.00842 0.00243 -0.0947 0.4337 0.5408 2.250 0.6970 0.00856 0.00254 -0.0942 0.4256 0.5453 2.500 0.7229 0.00865 0.00263 -0.0939 0.4187 0.5500 2.750 0.7466 0.00881 0.00276 -0.0932 0.4088 0.5559 3.000 0.7724 0.00890 0.00285 -0.0928 0.4015 0.5622 3.250 0.7963 0.00904 0.00297 -0.0922 0.3920 0.5693 3.500 0.8208 0.00915 0.00309 -0.0916 0.3820 0.5771 3.750 0.8413 0.00939 0.00324 -0.0903 0.3573 0.5837 4.000 0.8538 0.00985 0.00352 -0.0876 0.3204 0.5924 4.500 0.8884 0.01028 0.00392 -0.0838 0.2995 0.6138 4.750 0.9063 0.01052 0.00414 -0.0820 0.2920 0.6230 5.000 0.9259 0.01073 0.00436 -0.0806 0.2863 0.6320 5.250 0.9460 0.01093 0.00457 -0.0792 0.2808 0.6386 5.500 0.9651 0.01116 0.00481 -0.0778 0.2761 0.6450 5.750 0.9841 0.01141 0.00505 -0.0763 0.2714 0.6520 6.000 1.0049 0.01160 0.00527 -0.0752 0.2681 0.6590 6.250 1.0249 0.01182 0.00552 -0.0739 0.2637 0.6676 6.500 1.0429 0.01212 0.00580 -0.0724 0.2581 0.6729 6.750 1.0614 0.01240 0.00610 -0.0710 0.2529 0.6777 7.000 1.0811 0.01265 0.00637 -0.0698 0.2485 0.6828 7.250 1.0992 0.01297 0.00668 -0.0684 0.2428 0.6877 7.750 1.1347 0.01365 0.00737 -0.0656 0.2307 0.6961 8.000 1.1495 0.01412 0.00781 -0.0638 0.2210 0.7008 8.250 1.1641 0.01462 0.00828 -0.0621 0.2089 0.7054 8.500 1.1759 0.01526 0.00886 -0.0600 0.1947 0.7095 8.750 1.1881 0.01590 0.00946 -0.0581 0.1838 0.7141 9.000 1.2006 0.01655 0.01009 -0.0562 0.1753 0.7190 9.250 1.2143 0.01717 0.01071 -0.0546 0.1685 0.7238 9.750 1.2423 0.01843 0.01199 -0.0516 0.1584 0.7338 10.000 1.2571 0.01904 0.01263 -0.0502 0.1549 0.7399 10.250 1.2691 0.01982 0.01340 -0.0486 0.1495 0.7456 10.500 1.2834 0.02049 0.01411 -0.0473 0.1459 0.7523 10.750 1.2985 0.02112 0.01479 -0.0461 0.1432 0.7601 11.000 1.3123 0.02184 0.01554 -0.0449 0.1398 0.7684 11.250 1.3249 0.02263 0.01637 -0.0435 0.1366 0.7804 11.500 1.3374 0.02342 0.01723 -0.0421 0.1336 0.7965 12.000 1.3635 0.02476 0.01883 -0.0394 0.1299 0.8579 12.500 1.4089 0.02662 0.02090 -0.0415 0.1225 1.0000 12.750 1.4210 0.02767 0.02196 -0.0406 0.1194 1.0000 13.000 1.4349 0.02860 0.02293 -0.0398 0.1169 1.0000 13.250 1.4473 0.02966 0.02400 -0.0389 0.1135 1.0000 13.500 1.4581 0.03087 0.02521 -0.0380 0.1101 1.0000 13.750 1.4689 0.03210 0.02645 -0.0372 0.1065 1.0000 14.000 1.4806 0.03328 0.02766 -0.0364 0.1037 1.0000 14.250 1.4914 0.03454 0.02893 -0.0357 0.1002 1.0000 14.500 1.4985 0.03614 0.03051 -0.0347 0.0956 1.0000 14.750 1.5092 0.03745 0.03186 -0.0341 0.0920 1.0000 15.000 1.5181 0.03896 0.03339 -0.0334 0.0891 1.0000 15.250 1.5244 0.04070 0.03511 -0.0326 0.0843 1.0000 15.500 1.5316 0.04239 0.03683 -0.0320 0.0803 1.0000 15.750 1.5360 0.04436 0.03879 -0.0313 0.0753 1.0000 16.000 1.5396 0.04647 0.04091 -0.0307 0.0695 1.0000 16.250 1.5421 0.04871 0.04315 -0.0301 0.0640 1.0000 16.500 1.5389 0.05157 0.04597 -0.0294 0.0559 1.0000 16.750 1.5342 0.05466 0.04906 -0.0289 0.0484 1.0000 17.000 1.5293 0.05788 0.05228 -0.0286 0.0422 1.0000 17.250 1.5259 0.06105 0.05545 -0.0284 0.0378 1.0000 17.500 1.5258 0.06390 0.05835 -0.0284 0.0355 1.0000 17.750 1.5237 0.06707 0.06156 -0.0285 0.0333 1.0000 18.000 1.5251 0.06988 0.06444 -0.0287 0.0321 1.0000 18.250 1.5240 0.07307 0.06768 -0.0291 0.0305 1.0000 18.500 1.5205 0.07662 0.07129 -0.0296 0.0290 1.0000 18.750 1.5201 0.07985 0.07458 -0.0302 0.0281 1.0000 19.000 1.5191 0.08319 0.07800 -0.0309 0.0273 1.0000 19.250 1.5159 0.08690 0.08176 -0.0318 0.0262 1.0000