XFOIL Version 6.96 Calculated polar for: NACA 63 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 -1.0444 0.09303 0.08947 -0.0509 1.0000 0.0179 -19.500 -1.0512 0.08859 0.08496 -0.0530 1.0000 0.0181 -19.250 -1.0557 0.08443 0.08075 -0.0551 1.0000 0.0184 -19.000 -1.0629 0.08014 0.07638 -0.0569 1.0000 0.0184 -18.750 -1.0651 0.07646 0.07264 -0.0587 1.0000 0.0186 -18.500 -1.0689 0.07266 0.06877 -0.0603 1.0000 0.0187 -18.250 -1.0674 0.06952 0.06557 -0.0618 1.0000 0.0191 -18.000 -1.0669 0.06637 0.06236 -0.0631 1.0000 0.0193 -17.750 -1.0692 0.06300 0.05891 -0.0644 1.0000 0.0194 -17.500 -1.0690 0.05993 0.05577 -0.0655 1.0000 0.0195 -17.250 -1.0620 0.05762 0.05339 -0.0665 1.0000 0.0201 -17.000 -1.0580 0.05508 0.05078 -0.0674 1.0000 0.0203 -16.750 -1.0593 0.05209 0.04772 -0.0682 1.0000 0.0203 -16.500 -1.0510 0.05006 0.04562 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2.500 0.6381 0.00739 0.00223 -0.0792 0.5310 0.6130 2.750 0.6671 0.00743 0.00229 -0.0795 0.5265 0.6183 3.000 0.6963 0.00746 0.00237 -0.0798 0.5216 0.6235 3.250 0.7250 0.00753 0.00244 -0.0800 0.5165 0.6285 3.500 0.7534 0.00764 0.00252 -0.0802 0.5108 0.6330 3.750 0.7824 0.00765 0.00260 -0.0805 0.5048 0.6385 4.000 0.8105 0.00774 0.00268 -0.0806 0.4980 0.6441 4.250 0.8390 0.00783 0.00278 -0.0808 0.4922 0.6492 4.500 0.8676 0.00789 0.00287 -0.0810 0.4860 0.6544 5.000 0.9233 0.00808 0.00308 -0.0811 0.4683 0.6650 5.250 0.9505 0.00822 0.00319 -0.0811 0.4574 0.6700 5.500 0.9778 0.00833 0.00333 -0.0811 0.4480 0.6759 5.750 1.0052 0.00845 0.00347 -0.0811 0.4395 0.6815 6.000 1.0318 0.00863 0.00362 -0.0810 0.4289 0.6867 6.250 1.0583 0.00878 0.00378 -0.0809 0.4159 0.6920 6.500 1.0835 0.00901 0.00397 -0.0805 0.3987 0.6978 6.750 1.1079 0.00929 0.00419 -0.0801 0.3799 0.7036 7.000 1.1310 0.00962 0.00445 -0.0795 0.3565 0.7091 7.250 1.1513 0.01009 0.00481 -0.0784 0.3260 0.7150 7.500 1.1697 0.01066 0.00523 -0.0771 0.2941 0.7209 7.750 1.1864 0.01128 0.00570 -0.0755 0.2618 0.7265 8.000 1.2010 0.01194 0.00622 -0.0735 0.2297 0.7330 8.250 1.2139 0.01262 0.00676 -0.0713 0.2009 0.7395 8.500 1.2246 0.01325 0.00728 -0.0687 0.1758 0.7458 9.000 1.2371 0.01460 0.00847 -0.0621 0.1374 0.7601 9.250 1.2433 0.01535 0.00917 -0.0590 0.1208 0.7679 9.500 1.2498 0.01617 0.00995 -0.0563 0.1066 0.7763 9.750 1.2561 0.01705 0.01080 -0.0537 0.0943 0.7847 10.000 1.2633 0.01798 0.01171 -0.0514 0.0840 0.7941 10.250 1.2701 0.01897 0.01271 -0.0492 0.0748 0.8042 10.500 1.2769 0.02004 0.01378 -0.0472 0.0672 0.8155 10.750 1.2849 0.02108 0.01486 -0.0454 0.0615 0.8283 11.000 1.2936 0.02211 0.01594 -0.0437 0.0569 0.8432 11.250 1.2999 0.02329 0.01717 -0.0419 0.0526 0.8629 11.500 1.3070 0.02432 0.01832 -0.0400 0.0495 0.8938 11.750 1.3157 0.02545 0.01960 -0.0389 0.0464 1.0000 12.000 1.3254 0.02676 0.02092 -0.0379 0.0437 1.0000 12.250 1.3347 0.02811 0.02229 -0.0370 0.0413 1.0000 12.500 1.3404 0.02978 0.02395 -0.0360 0.0388 1.0000 12.750 1.3509 0.03111 0.02533 -0.0353 0.0372 1.0000 13.000 1.3589 0.03267 0.02691 -0.0346 0.0355 1.0000 13.250 1.3640 0.03451 0.02876 -0.0338 0.0337 1.0000 13.500 1.3726 0.03612 0.03042 -0.0332 0.0326 1.0000 13.750 1.3810 0.03778 0.03211 -0.0327 0.0314 1.0000 14.000 1.3875 0.03965 0.03401 -0.0323 0.0302 1.0000 14.250 1.3899 0.04198 0.03637 -0.0318 0.0289 1.0000 14.500 1.3981 0.04382 0.03826 -0.0315 0.0282 1.0000 14.750 1.4058 0.04572 0.04022 -0.0313 0.0274 1.0000 15.000 1.4120 0.04783 0.04236 -0.0312 0.0267 1.0000 15.250 1.4164 0.05017 0.04474 -0.0311 0.0258 1.0000 15.500 1.4181 0.05286 0.04747 -0.0311 0.0250 1.0000 15.750 1.4211 0.05547 0.05014 -0.0312 0.0244 1.0000 16.000 1.4279 0.05768 0.05241 -0.0313 0.0240 1.0000 16.250 1.4333 0.06012 0.05492 -0.0316 0.0234 1.0000 16.500 1.4379 0.06268 0.05753 -0.0319 0.0228 1.0000 16.750 1.4405 0.06554 0.06043 -0.0324 0.0223 1.0000 17.000 1.4409 0.06872 0.06367 -0.0329 0.0218 1.0000 17.250 1.4383 0.07235 0.06736 -0.0336 0.0212 1.0000 17.500 1.4391 0.07564 0.07072 -0.0344 0.0208 1.0000 17.750 1.4422 0.07864 0.07380 -0.0352 0.0206 1.0000 18.000 1.4448 0.08175 0.07698 -0.0360 0.0202 1.0000 18.250 1.4464 0.08503 0.08033 -0.0370 0.0198 1.0000 18.500 1.4480 0.08838 0.08374 -0.0380 0.0195 1.0000 18.750 1.4472 0.09214 0.08758 -0.0393 0.0192 1.0000 19.000 1.4467 0.09586 0.09136 -0.0406 0.0188 1.0000 19.250 1.4443 0.09992 0.09549 -0.0421 0.0185 1.0000