XFOIL Version 6.96 Calculated polar for: WORTMANN FX 3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.4499 0.11374 0.11061 -0.1246 0.8401 0.0147 -17.500 -0.4948 0.09957 0.09624 -0.1325 0.8405 0.0144 -17.250 -0.5371 0.08763 0.08408 -0.1394 0.8410 0.0142 -17.000 -0.5638 0.07949 0.07575 -0.1442 0.8414 0.0141 -16.750 -0.5825 0.07319 0.06927 -0.1477 0.8419 0.0141 -16.500 -0.5963 0.06807 0.06398 -0.1504 0.8424 0.0142 -16.250 -0.6059 0.06384 0.05958 -0.1524 0.8429 0.0143 -16.000 -0.6122 0.06027 0.05585 -0.1539 0.8434 0.0144 -15.750 -0.6191 0.05689 0.05230 -0.1549 0.8439 0.0145 -15.500 -0.6331 0.05287 0.04805 -0.1551 0.8445 0.0147 -15.250 -0.6376 0.05004 0.04507 -0.1552 0.8451 0.0150 -15.000 -0.6357 0.04800 0.04292 -0.1552 0.8457 0.0153 -14.750 -0.6307 0.04635 0.04120 -0.1551 0.8462 0.0156 -14.500 -0.6238 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0.0257 0.7418 11.750 1.2107 0.04568 0.03842 -0.0752 0.0237 0.7412 12.000 1.2213 0.04721 0.03996 -0.0741 0.0218 0.7406 12.250 1.2302 0.04889 0.04171 -0.0729 0.0205 0.7401 12.500 1.2442 0.05018 0.04307 -0.0723 0.0196 0.7397 12.750 1.2561 0.05162 0.04457 -0.0716 0.0187 0.7392 13.000 1.2664 0.05317 0.04619 -0.0706 0.0179 0.7389 13.250 1.2748 0.05489 0.04795 -0.0695 0.0171 0.7385 13.500 1.2779 0.05709 0.05021 -0.0679 0.0164 0.7382 13.750 1.2780 0.05956 0.05277 -0.0660 0.0158 0.7379 14.000 1.2882 0.06120 0.05449 -0.0652 0.0155 0.7376 14.250 1.2969 0.06297 0.05634 -0.0642 0.0151 0.7373 14.500 1.3043 0.06484 0.05830 -0.0632 0.0147 0.7371 14.750 1.3110 0.06680 0.06034 -0.0622 0.0143 0.7369 15.000 1.3180 0.06876 0.06239 -0.0614 0.0139 0.7367 15.250 1.3243 0.07086 0.06456 -0.0606 0.0135 0.7366 15.500 1.3302 0.07300 0.06676 -0.0599 0.0131 0.7366 15.750 1.3344 0.07533 0.06914 -0.0592 0.0128 0.7366 16.000 1.3357 0.07778 0.07166 -0.0580 0.0124 0.7365 16.250 1.3391 0.08011 0.07410 -0.0570 0.0121 0.7364 16.500 1.3444 0.08250 0.07662 -0.0566 0.0119 0.7363 16.750 1.3489 0.08500 0.07924 -0.0563 0.0117 0.7362 17.000 1.3526 0.08759 0.08197 -0.0561 0.0116 0.7360 17.250 1.3553 0.09033 0.08484 -0.0558 0.0114 0.7359 17.500 1.3572 0.09318 0.08781 -0.0557 0.0112 0.7358 17.750 1.3581 0.09620 0.09097 -0.0558 0.0110 0.7356 18.000 1.3582 0.09935 0.09424 -0.0559 0.0108 0.7355 18.250 1.3579 0.10262 0.09763 -0.0563 0.0107 0.7354 18.500 1.3567 0.10605 0.10119 -0.0568 0.0105 0.7352 18.750 1.3546 0.10970 0.10497 -0.0576 0.0104 0.7351 19.000 1.3515 0.11356 0.10896 -0.0587 0.0103 0.7350 19.250 1.3483 0.11752 0.11305 -0.0600 0.0101 0.7349 19.500 1.3438 0.12172 0.11738 -0.0615 0.0100 0.7347 19.750 1.3407 0.12576 0.12151 -0.0633 0.0099 0.7346 20.000 1.3352 0.13025 0.12613 -0.0652 0.0098 0.7345