XFOIL Version 6.96 Calculated polar for: NACA 66-018 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9785 0.10119 0.09828 -0.0516 1.0000 0.0136 -19.500 -0.9993 0.09413 0.09105 -0.0550 1.0000 0.0135 -19.250 -1.0149 0.08812 0.08489 -0.0577 1.0000 0.0136 -19.000 -1.0253 0.08304 0.07968 -0.0600 1.0000 0.0136 -18.750 -1.0392 0.07778 0.07426 -0.0619 1.0000 0.0137 -18.500 -1.0487 0.07331 0.06967 -0.0632 1.0000 0.0136 -18.250 -1.0534 0.06955 0.06578 -0.0644 1.0000 0.0137 -18.000 -1.0572 0.06600 0.06211 -0.0654 1.0000 0.0138 -17.750 -1.0632 0.06245 0.05843 -0.0657 1.0000 0.0137 -17.500 -1.0627 0.05969 0.05557 -0.0663 1.0000 0.0138 -17.250 -1.0711 0.05591 0.05161 -0.0660 0.9738 0.0139 -17.000 -1.0630 0.05233 0.04788 -0.0686 0.9658 0.0142 -16.750 -1.0449 0.04954 0.04497 -0.0722 0.9587 0.0143 -16.500 -1.0261 0.04699 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0.0049 0.7446 0.7100 -2.250 -0.2633 0.00720 0.00301 0.0047 0.7435 0.7146 -2.000 -0.2339 0.00719 0.00303 0.0042 0.7426 0.7189 -1.750 -0.2044 0.00726 0.00312 0.0037 0.7417 0.7222 -1.500 -0.1751 0.00731 0.00316 0.0032 0.7408 0.7248 -1.250 -0.1460 0.00733 0.00317 0.0027 0.7399 0.7267 -1.000 -0.1170 0.00738 0.00320 0.0022 0.7390 0.7289 -0.750 -0.0881 0.00745 0.00324 0.0018 0.7382 0.7307 -0.500 -0.0590 0.00738 0.00319 0.0012 0.7373 0.7331 -0.250 -0.0296 0.00737 0.00318 0.0006 0.7365 0.7345 0.000 -0.0001 0.00737 0.00319 0.0000 0.7356 0.7356 0.250 0.0295 0.00737 0.00318 -0.0006 0.7345 0.7365 0.500 0.0589 0.00737 0.00318 -0.0012 0.7332 0.7373 0.750 0.0882 0.00743 0.00322 -0.0018 0.7307 0.7382 1.000 0.1171 0.00738 0.00319 -0.0022 0.7288 0.7390 1.250 0.1461 0.00733 0.00317 -0.0027 0.7267 0.7399 1.500 0.1751 0.00731 0.00316 -0.0032 0.7248 0.7408 1.750 0.2044 0.00726 0.00312 -0.0037 0.7222 0.7417 2.000 0.2339 0.00719 0.00304 -0.0042 0.7189 0.7426 2.250 0.2633 0.00717 0.00299 -0.0047 0.7145 0.7435 2.500 0.2913 0.00708 0.00293 -0.0049 0.7096 0.7446 2.750 0.3200 0.00700 0.00287 -0.0053 0.7048 0.7455 3.000 0.3488 0.00695 0.00277 -0.0056 0.6986 0.7464 3.250 0.3761 0.00685 0.00271 -0.0057 0.6896 0.7471 3.500 0.4032 0.00678 0.00261 -0.0056 0.6770 0.7478 3.750 0.4304 0.00671 0.00254 -0.0057 0.6658 0.7492 4.000 0.4575 0.00667 0.00254 -0.0057 0.6523 0.7505 4.250 0.4826 0.00670 0.00254 -0.0054 0.6244 0.7517 4.500 0.4869 0.00737 0.00277 -0.0010 0.5218 0.7532 4.750 0.4889 0.00813 0.00318 0.0035 0.4404 0.7548 5.000 0.4887 0.00880 0.00356 0.0085 0.3694 0.7565 5.250 0.4819 0.00935 0.00388 0.0149 0.3133 0.7584 5.500 0.4772 0.01009 0.00438 0.0205 0.2583 0.7603 5.750 0.4758 0.01091 0.00494 0.0252 0.2029 0.7621 6.000 0.4770 0.01174 0.00551 0.0292 0.1465 0.7637 6.250 0.4809 0.01254 0.00607 0.0327 0.0976 0.7652 6.500 0.4888 0.01322 0.00658 0.0355 0.0614 0.7677 6.750 0.5021 0.01374 0.00703 0.0374 0.0452 0.7698 7.000 0.5185 0.01417 0.00744 0.0388 0.0391 0.7717 7.250 0.5352 0.01460 0.00785 0.0402 0.0354 0.7736 7.500 0.5530 0.01499 0.00826 0.0413 0.0327 0.7755 7.750 0.5705 0.01541 0.00868 0.0425 0.0307 0.7775 8.000 0.5863 0.01592 0.00919 0.0439 0.0285 0.7794 8.250 0.6051 0.01630 0.00958 0.0448 0.0271 0.7811 8.500 0.6227 0.01674 0.01002 0.0459 0.0261 0.7830 8.750 0.6379 0.01726 0.01057 0.0472 0.0249 0.7858 9.000 0.6532 0.01781 0.01117 0.0486 0.0239 0.7883 9.250 0.6709 0.01825 0.01165 0.0496 0.0232 0.7906 9.500 0.6883 0.01872 0.01214 0.0506 0.0224 0.7931 9.750 0.7052 0.01923 0.01267 0.0516 0.0217 0.7955 10.000 0.7199 0.01987 0.01332 0.0529 0.0210 0.7979 10.250 0.7318 0.02066 0.01413 0.0544 0.0204 0.8003 10.500 0.7464 0.02128 0.01482 0.0557 0.0199 0.8037 10.750 0.7607 0.02194 0.01554 0.0569 0.0197 0.8067 11.000 0.7773 0.02250 0.01615 0.0578 0.0193 0.8098 11.250 0.7907 0.02326 0.01695 0.0590 0.0191 0.8129 11.500 0.8067 0.02388 0.01760 0.0599 0.0186 0.8157 11.750 0.8220 0.02455 0.01830 0.0608 0.0181 0.8190 12.000 0.8347 0.02535 0.01916 0.0620 0.0178 0.8228 12.250 0.8486 0.02610 0.01994 0.0630 0.0173 0.8266 12.500 0.8590 0.02713 0.02101 0.0644 0.0172 0.8305 12.750 0.8650 0.02854 0.02247 0.0661 0.0168 0.8339 13.000 0.8788 0.02934 0.02336 0.0670 0.0167 0.8385 13.250 0.8916 0.03023 0.02433 0.0679 0.0166 0.8430 13.500 0.9045 0.03116 0.02534 0.0688 0.0164 0.8475 13.750 0.9172 0.03214 0.02637 0.0696 0.0161 0.8516 14.000 0.9284 0.03319 0.02751 0.0706 0.0161 0.8570 14.250 0.9399 0.03424 0.02865 0.0715 0.0159 0.8625 14.500 0.9508 0.03541 0.02990 0.0724 0.0158 0.8678 14.750 0.9605 0.03661 0.03120 0.0733 0.0156 0.8742 15.000 0.9702 0.03782 0.03250 0.0742 0.0154 0.8815 15.250 0.9795 0.03906 0.03384 0.0749 0.0152 0.8892 15.500 0.9870 0.04050 0.03539 0.0759 0.0151 0.8985 15.750 0.9950 0.04187 0.03688 0.0766 0.0150 0.9091 16.000 1.0019 0.04338 0.03849 0.0773 0.0147 0.9220 16.250 1.0111 0.04504 0.04027 0.0773 0.0146 0.9365 16.500 1.0278 0.04706 0.04242 0.0752 0.0146 0.9505 17.000 1.0663 0.05233 0.04789 0.0680 0.0142 0.9662 17.250 1.0799 0.05544 0.05113 0.0649 0.0140 0.9973 17.500 1.0787 0.05821 0.05400 0.0652 0.0139 1.0000 17.750 1.0646 0.06252 0.05850 0.0656 0.0138 1.0000 18.000 1.0614 0.06585 0.06195 0.0647 0.0136 1.0000 18.250 1.0560 0.06947 0.06569 0.0641 0.0137 1.0000 18.500 1.0526 0.07314 0.06948 0.0628 0.0136 1.0000 18.750 1.0438 0.07760 0.07408 0.0613 0.0135 1.0000 19.000 1.0346 0.08224 0.07885 0.0595 0.0135 1.0000 19.250 1.0221 0.08753 0.08428 0.0573 0.0135 1.0000