XFOIL Version 6.96 Calculated polar for: NACA 64(3)-418 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 -1.0159 0.09241 0.08912 -0.0574 1.0000 0.0185 -19.500 -1.0241 0.08761 0.08423 -0.0598 1.0000 0.0186 -19.250 -1.0306 0.08315 0.07968 -0.0620 1.0000 0.0187 -19.000 -1.0362 0.07884 0.07526 -0.0642 1.0000 0.0189 -18.750 -1.0415 0.07481 0.07114 -0.0659 1.0000 0.0190 -18.500 -1.0431 0.07127 0.06752 -0.0676 1.0000 0.0191 -18.250 -1.0449 0.06777 0.06392 -0.0691 1.0000 0.0193 -18.000 -1.0454 0.06452 0.06058 -0.0705 1.0000 0.0195 -17.750 -1.0453 0.06149 0.05746 -0.0716 1.0000 0.0196 -17.500 -1.0427 0.05874 0.05463 -0.0727 1.0000 0.0197 -17.250 -1.0399 0.05605 0.05186 -0.0737 1.0000 0.0198 -17.000 -1.0443 0.05296 0.04868 -0.0741 1.0000 0.0201 -16.750 -1.0428 0.05042 0.04609 -0.0746 1.0000 0.0204 -16.500 -1.0396 0.04806 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0.6041 2.500 0.6356 0.00752 0.00231 -0.0801 0.5443 0.6084 2.750 0.6649 0.00755 0.00237 -0.0805 0.5418 0.6124 3.000 0.6941 0.00756 0.00244 -0.0808 0.5392 0.6177 3.250 0.7230 0.00760 0.00251 -0.0811 0.5358 0.6230 3.500 0.7513 0.00769 0.00258 -0.0813 0.5304 0.6279 3.750 0.7798 0.00773 0.00265 -0.0815 0.5249 0.6330 4.000 0.8085 0.00774 0.00271 -0.0818 0.5192 0.6385 4.250 0.8360 0.00784 0.00280 -0.0818 0.5117 0.6441 4.500 0.8648 0.00788 0.00287 -0.0821 0.5070 0.6490 4.750 0.8932 0.00792 0.00296 -0.0823 0.5013 0.6551 5.000 0.9202 0.00804 0.00307 -0.0823 0.4933 0.6612 5.250 0.9485 0.00809 0.00316 -0.0825 0.4848 0.6668 5.500 0.9752 0.00821 0.00328 -0.0824 0.4761 0.6730 5.750 1.0033 0.00827 0.00340 -0.0825 0.4688 0.6794 6.000 1.0297 0.00842 0.00354 -0.0824 0.4584 0.6855 6.250 1.0562 0.00854 0.00368 -0.0823 0.4457 0.6920 6.500 1.0812 0.00874 0.00386 -0.0820 0.4267 0.6988 6.750 1.1001 0.00927 0.00417 -0.0806 0.3773 0.7050 7.000 1.1114 0.01017 0.00478 -0.0781 0.3166 0.7119 7.250 1.1203 0.01114 0.00545 -0.0753 0.2577 0.7192 7.500 1.1282 0.01204 0.00610 -0.0722 0.2097 0.7263 7.750 1.1345 0.01278 0.00669 -0.0688 0.1746 0.7343 8.000 1.1394 0.01347 0.00725 -0.0652 0.1494 0.7422 8.250 1.1454 0.01417 0.00789 -0.0619 0.1285 0.7503 8.500 1.1523 0.01491 0.00856 -0.0589 0.1112 0.7589 8.750 1.1601 0.01566 0.00927 -0.0562 0.0970 0.7672 9.000 1.1683 0.01645 0.01004 -0.0538 0.0850 0.7763 9.250 1.1764 0.01730 0.01088 -0.0515 0.0746 0.7852 9.500 1.1847 0.01821 0.01178 -0.0494 0.0654 0.7951 9.750 1.1927 0.01917 0.01274 -0.0473 0.0572 0.8051 10.250 1.2091 0.02123 0.01484 -0.0436 0.0453 0.8283 10.500 1.2179 0.02228 0.01593 -0.0419 0.0410 0.8415 10.750 1.2271 0.02332 0.01703 -0.0404 0.0379 0.8569 11.000 1.2343 0.02450 0.01826 -0.0387 0.0351 0.8752 11.250 1.2430 0.02556 0.01941 -0.0371 0.0332 0.8958 11.500 1.2492 0.02668 0.02062 -0.0352 0.0314 0.9252 11.750 1.2606 0.02795 0.02200 -0.0348 0.0296 1.0000 12.000 1.2716 0.02923 0.02330 -0.0340 0.0282 1.0000 12.250 1.2803 0.03069 0.02477 -0.0332 0.0267 1.0000 12.500 1.2882 0.03226 0.02637 -0.0323 0.0254 1.0000 12.750 1.2988 0.03365 0.02780 -0.0318 0.0243 1.0000 13.000 1.3076 0.03521 0.02938 -0.0311 0.0232 1.0000 13.250 1.3124 0.03715 0.03134 -0.0304 0.0221 1.0000 13.500 1.3224 0.03870 0.03294 -0.0299 0.0213 1.0000 13.750 1.3319 0.04032 0.03460 -0.0296 0.0205 1.0000 14.000 1.3395 0.04216 0.03647 -0.0292 0.0197 1.0000 14.250 1.3435 0.04437 0.03870 -0.0287 0.0189 1.0000 14.500 1.3505 0.04636 0.04074 -0.0285 0.0183 1.0000 14.750 1.3587 0.04825 0.04269 -0.0283 0.0180 1.0000 15.000 1.3659 0.05030 0.04479 -0.0282 0.0175 1.0000 15.250 1.3730 0.05236 0.04689 -0.0281 0.0169 1.0000 15.500 1.3784 0.05466 0.04923 -0.0281 0.0165 1.0000 15.750 1.3817 0.05725 0.05186 -0.0282 0.0161 1.0000 16.000 1.3814 0.06030 0.05498 -0.0283 0.0157 1.0000 16.250 1.3866 0.06279 0.05753 -0.0286 0.0155 1.0000 16.500 1.3932 0.06512 0.05993 -0.0289 0.0153 1.0000 16.750 1.3968 0.06788 0.06276 -0.0293 0.0151 1.0000 17.000 1.4016 0.07053 0.06547 -0.0297 0.0149 1.0000 17.250 1.4044 0.07349 0.06849 -0.0303 0.0147 1.0000 17.500 1.4081 0.07634 0.07141 -0.0309 0.0145 1.0000 17.750 1.4097 0.07954 0.07468 -0.0317 0.0143 1.0000 18.000 1.4120 0.08269 0.07789 -0.0325 0.0141 1.0000 18.250 1.4134 0.08602 0.08129 -0.0334 0.0140 1.0000 18.500 1.4133 0.08961 0.08494 -0.0345 0.0138 1.0000 18.750 1.4127 0.09329 0.08870 -0.0357 0.0136 1.0000 19.000 1.4108 0.09726 0.09274 -0.0370 0.0136 1.0000 19.250 1.4052 0.10182 0.09737 -0.0387 0.0133 1.0000