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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.7562 0.12045 0.11584 -0.0421 1.0000 0.0276 -18.250 -0.7999 0.10742 0.10252 -0.0501 1.0000 0.0276 -18.000 -0.8259 0.09869 0.09354 -0.0553 1.0000 0.0277 -17.750 -0.8448 0.09158 0.08622 -0.0595 1.0000 0.0279 -17.500 -0.8565 0.08604 0.08051 -0.0625 1.0000 0.0280 -17.250 -0.8572 0.08251 0.07694 -0.0642 1.0000 0.0284 -17.000 -0.8597 0.07872 0.07308 -0.0660 1.0000 0.0286 -16.750 -0.8618 0.07507 0.06935 -0.0678 1.0000 0.0289 -16.500 -0.8634 0.07158 0.06577 -0.0693 1.0000 0.0292 -16.250 -0.8646 0.06823 0.06232 -0.0708 1.0000 0.0295 -16.000 -0.8650 0.06505 0.05904 -0.0720 1.0000 0.0299 -15.750 -0.8650 0.06203 0.05592 -0.0731 1.0000 0.0303 -15.500 -0.8638 0.05922 0.05299 -0.0740 1.0000 0.0307 -15.250 -0.8628 0.05645 0.05008 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0.6414 0.5818 -1.000 0.2050 0.01283 0.00501 -0.0701 0.6368 0.5866 -0.750 0.2339 0.01285 0.00496 -0.0704 0.6326 0.5921 -0.500 0.2624 0.01287 0.00497 -0.0706 0.6271 0.5971 -0.250 0.2906 0.01289 0.00502 -0.0707 0.6223 0.6013 0.000 0.3193 0.01293 0.00504 -0.0708 0.6182 0.6064 0.250 0.3482 0.01298 0.00503 -0.0711 0.6141 0.6119 0.500 0.3764 0.01301 0.00511 -0.0713 0.6088 0.6163 0.750 0.4044 0.01306 0.00518 -0.0713 0.6040 0.6209 1.000 0.4331 0.01312 0.00521 -0.0715 0.6000 0.6263 1.250 0.4619 0.01318 0.00526 -0.0718 0.5959 0.6319 1.500 0.4896 0.01324 0.00538 -0.0718 0.5908 0.6359 1.750 0.5176 0.01331 0.00548 -0.0719 0.5861 0.6408 2.000 0.5462 0.01339 0.00553 -0.0721 0.5821 0.6465 2.250 0.5745 0.01348 0.00564 -0.0723 0.5776 0.6520 2.500 0.6018 0.01356 0.00581 -0.0722 0.5725 0.6564 2.750 0.6297 0.01364 0.00592 -0.0723 0.5678 0.6615 3.000 0.6584 0.01374 0.00598 -0.0725 0.5638 0.6675 3.250 0.6853 0.01384 0.00618 -0.0724 0.5585 0.6725 3.500 0.7124 0.01394 0.00635 -0.0723 0.5531 0.6777 3.750 0.7403 0.01404 0.00645 -0.0724 0.5484 0.6835 4.000 0.7680 0.01416 0.00661 -0.0725 0.5434 0.6891 4.250 0.7942 0.01427 0.00683 -0.0723 0.5376 0.6940 4.500 0.8213 0.01438 0.00698 -0.0722 0.5322 0.7001 4.750 0.8489 0.01451 0.00712 -0.0723 0.5269 0.7066 5.000 0.8742 0.01463 0.00737 -0.0719 0.5202 0.7114 5.250 0.9006 0.01474 0.00751 -0.0716 0.5138 0.7172 5.500 0.9264 0.01488 0.00771 -0.0714 0.5059 0.7240 5.750 0.9513 0.01499 0.00788 -0.0709 0.4976 0.7294 6.000 0.9759 0.01513 0.00811 -0.0704 0.4894 0.7356 6.250 1.0009 0.01528 0.00829 -0.0701 0.4802 0.7424 6.500 1.0236 0.01542 0.00853 -0.0692 0.4692 0.7481 6.750 1.0455 0.01559 0.00873 -0.0682 0.4555 0.7550 7.000 1.0666 0.01579 0.00894 -0.0672 0.4400 0.7621 7.250 1.0860 0.01602 0.00921 -0.0658 0.4244 0.7684 7.500 1.1054 0.01631 0.00952 -0.0646 0.4086 0.7761 7.750 1.1226 0.01662 0.00986 -0.0629 0.3910 0.7832 8.000 1.1375 0.01701 0.01026 -0.0610 0.3704 0.7913 8.250 1.1477 0.01752 0.01071 -0.0584 0.3468 0.7995 8.500 1.1516 0.01811 0.01126 -0.0547 0.3222 0.8088 8.750 1.1522 0.01896 0.01202 -0.0509 0.2972 0.8189 9.000 1.1528 0.01997 0.01295 -0.0475 0.2716 0.8306 9.250 1.1507 0.02117 0.01408 -0.0440 0.2476 0.8431 9.500 1.1496 0.02245 0.01532 -0.0409 0.2240 0.8578 9.750 1.1476 0.02387 0.01670 -0.0380 0.2028 0.8765 10.000 1.1457 0.02536 0.01816 -0.0353 0.1833 0.9032 10.250 1.1464 0.02680 0.01962 -0.0334 0.1650 1.0000 10.500 1.1496 0.02864 0.02138 -0.0323 0.1473 1.0000 10.750 1.1532 0.03052 0.02318 -0.0314 0.1321 1.0000 11.000 1.1567 0.03245 0.02506 -0.0305 0.1186 1.0000 11.250 1.1604 0.03442 0.02699 -0.0297 0.1069 1.0000 11.500 1.1642 0.03643 0.02898 -0.0290 0.0972 1.0000 11.750 1.1673 0.03855 0.03107 -0.0284 0.0890 1.0000 12.000 1.1726 0.04053 0.03306 -0.0279 0.0818 1.0000 12.250 1.1764 0.04272 0.03525 -0.0275 0.0759 1.0000 12.500 1.1811 0.04488 0.03744 -0.0272 0.0708 1.0000 12.750 1.1851 0.04717 0.03975 -0.0270 0.0665 1.0000 13.000 1.1901 0.04942 0.04204 -0.0269 0.0625 1.0000 13.250 1.1927 0.05199 0.04462 -0.0268 0.0594 1.0000 13.500 1.1986 0.05425 0.04695 -0.0268 0.0565 1.0000 13.750 1.2028 0.05674 0.04950 -0.0270 0.0539 1.0000 14.000 1.2044 0.05960 0.05237 -0.0272 0.0516 1.0000 14.250 1.2103 0.06201 0.05487 -0.0274 0.0494 1.0000 14.500 1.2143 0.06468 0.05761 -0.0277 0.0474 1.0000 14.750 1.2169 0.06758 0.06055 -0.0282 0.0458 1.0000 15.000 1.2191 0.07056 0.06356 -0.0287 0.0443 1.0000 15.250 1.2238 0.07330 0.06641 -0.0292 0.0427 1.0000 15.500 1.2278 0.07616 0.06935 -0.0298 0.0411 1.0000 15.750 1.2302 0.07927 0.07252 -0.0306 0.0399 1.0000 16.000 1.2313 0.08259 0.07586 -0.0314 0.0389 1.0000 16.250 1.2354 0.08555 0.07892 -0.0322 0.0377 1.0000 16.500 1.2393 0.08857 0.08203 -0.0330 0.0366 1.0000 16.750 1.2422 0.09177 0.08532 -0.0340 0.0355 1.0000 17.000 1.2446 0.09506 0.08867 -0.0351 0.0346 1.0000 17.250 1.2461 0.09852 0.09217 -0.0363 0.0338 1.0000