XFOIL Version 6.96 Calculated polar for: NACA 64-012A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.7891 0.07868 0.07096 -0.0314 1.0000 0.0480 -10.750 -0.8055 0.07444 0.06657 -0.0317 1.0000 0.0479 -10.500 -0.8210 0.07066 0.06261 -0.0307 1.0000 0.0478 -10.250 -0.8336 0.06707 0.05879 -0.0292 1.0000 0.0478 -10.000 -0.8424 0.06345 0.05487 -0.0276 1.0000 0.0479 -9.750 -0.8458 0.05986 0.05104 -0.0261 1.0000 0.0484 -9.500 -0.8413 0.05674 0.04774 -0.0250 1.0000 0.0496 -9.250 -0.8334 0.05409 0.04495 -0.0238 1.0000 0.0510 -9.000 -0.8262 0.05132 0.04191 -0.0224 1.0000 0.0525 -8.750 -0.8173 0.04843 0.03867 -0.0208 1.0000 0.0537 -8.500 -0.8051 0.04552 0.03537 -0.0193 1.0000 0.0546 -8.250 -0.7893 0.04277 0.03223 -0.0180 1.0000 0.0558 -8.000 -0.7701 0.04025 0.02930 -0.0169 1.0000 0.0573 -7.750 -0.7492 0.03811 0.02673 -0.0159 1.0000 0.0600 -7.500 -0.7265 0.03617 0.02483 -0.0155 1.0000 0.0637 -7.250 -0.7013 0.03445 0.02295 -0.0149 1.0000 0.0677 -7.000 -0.6731 0.03286 0.02108 -0.0144 1.0000 0.0718 -6.750 -0.6507 0.03140 0.01973 -0.0136 1.0000 0.0781 -6.500 -0.6286 0.03021 0.01833 -0.0124 1.0000 0.0858 -6.250 -0.6123 0.02886 0.01707 -0.0108 1.0000 0.0936 -6.000 -0.5979 0.02764 0.01587 -0.0089 1.0000 0.1057 -5.750 -0.5858 0.02635 0.01466 -0.0066 1.0000 0.1211 -5.500 -0.5763 0.02493 0.01347 -0.0042 1.0000 0.1481 -5.250 -0.5711 0.02314 0.01221 -0.0013 1.0000 0.2090 -5.000 -0.5734 0.02109 0.01152 0.0030 1.0000 0.3808 -4.750 -0.5653 0.02076 0.01182 0.0076 1.0000 0.5401 -4.500 -0.5530 0.02090 0.01205 0.0116 1.0000 0.6071 -4.250 -0.5398 0.02118 0.01232 0.0155 1.0000 0.6553 -4.000 -0.5274 0.02175 0.01290 0.0202 1.0000 0.7022 -3.750 -0.5113 0.02249 0.01361 0.0247 1.0000 0.7408 -3.500 -0.4948 0.02281 0.01383 0.0281 1.0000 0.7678 -3.250 -0.4752 0.02286 0.01373 0.0300 1.0000 0.7847 -3.000 -0.4570 0.02274 0.01347 0.0317 1.0000 0.7991 -2.750 -0.4392 0.02257 0.01314 0.0331 1.0000 0.8128 -2.500 -0.4210 0.02242 0.01286 0.0344 1.0000 0.8257 -2.250 -0.3838 0.02243 0.01269 0.0321 0.9940 0.8355 -2.000 -0.3426 0.02241 0.01247 0.0287 0.9850 0.8456 -1.750 -0.3029 0.02236 0.01226 0.0256 0.9754 0.8560 -1.250 -0.2194 0.02235 0.01200 0.0188 0.9578 0.8740 -1.000 -0.1748 0.02238 0.01194 0.0150 0.9498 0.8823 -0.750 -0.1330 0.02238 0.01186 0.0116 0.9409 0.8912 -0.500 -0.0869 0.02238 0.01181 0.0074 0.9336 0.8999 -0.250 -0.0440 0.02239 0.01179 0.0038 0.9247 0.9079 0.000 0.0000 0.02237 0.01175 0.0000 0.9173 0.9173 0.250 0.0440 0.02239 0.01179 -0.0038 0.9079 0.9247 0.500 0.0869 0.02238 0.01181 -0.0074 0.8999 0.9336 0.750 0.1330 0.02237 0.01186 -0.0116 0.8912 0.9409 1.000 0.1748 0.02238 0.01194 -0.0150 0.8824 0.9498 1.250 0.2194 0.02235 0.01200 -0.0188 0.8740 0.9579 1.500 0.2601 0.02238 0.01216 -0.0221 0.8642 0.9668 1.750 0.3030 0.02235 0.01226 -0.0256 0.8560 0.9754 2.000 0.3426 0.02240 0.01247 -0.0287 0.8456 0.9850 2.250 0.3838 0.02243 0.01269 -0.0321 0.8355 0.9940 2.500 0.4210 0.02242 0.01285 -0.0344 0.8257 1.0000 2.750 0.4391 0.02257 0.01314 -0.0331 0.8128 1.0000 3.000 0.4569 0.02274 0.01344 -0.0317 0.7991 1.0000 3.250 0.4751 0.02286 0.01373 -0.0300 0.7846 1.0000 3.500 0.4947 0.02281 0.01383 -0.0281 0.7678 1.0000 3.750 0.5113 0.02249 0.01361 -0.0247 0.7408 1.0000 4.000 0.5273 0.02175 0.01289 -0.0202 0.7022 1.0000 4.250 0.5398 0.02118 0.01232 -0.0155 0.6553 1.0000 4.500 0.5530 0.02090 0.01205 -0.0116 0.6071 1.0000 4.750 0.5653 0.02076 0.01182 -0.0076 0.5401 1.0000 5.000 0.5734 0.02109 0.01152 -0.0030 0.3807 1.0000 5.250 0.5711 0.02314 0.01220 0.0013 0.2090 1.0000 5.500 0.5763 0.02493 0.01346 0.0042 0.1481 1.0000 5.750 0.5858 0.02635 0.01466 0.0066 0.1211 1.0000 6.000 0.5979 0.02764 0.01587 0.0089 0.1057 1.0000 6.250 0.6123 0.02886 0.01707 0.0108 0.0936 1.0000 6.500 0.6286 0.03021 0.01833 0.0124 0.0858 1.0000 7.000 0.6732 0.03286 0.02108 0.0144 0.0718 1.0000 7.250 0.7013 0.03445 0.02295 0.0149 0.0677 1.0000 7.500 0.7266 0.03617 0.02483 0.0155 0.0637 1.0000 7.750 0.7492 0.03811 0.02673 0.0159 0.0600 1.0000 8.000 0.7701 0.04025 0.02930 0.0169 0.0573 1.0000 8.250 0.7894 0.04278 0.03223 0.0180 0.0558 1.0000 8.500 0.8052 0.04552 0.03537 0.0193 0.0546 1.0000 8.750 0.8174 0.04843 0.03867 0.0208 0.0537 1.0000 9.000 0.8263 0.05132 0.04191 0.0223 0.0525 1.0000 9.250 0.8336 0.05410 0.04496 0.0238 0.0510 1.0000 9.500 0.8415 0.05674 0.04775 0.0249 0.0495 1.0000 9.750 0.8460 0.05987 0.05105 0.0260 0.0484 1.0000 10.000 0.8426 0.06346 0.05488 0.0276 0.0479 1.0000 10.250 0.8338 0.06709 0.05881 0.0292 0.0478 1.0000 10.500 0.8212 0.07069 0.06264 0.0307 0.0478 1.0000 10.750 0.8058 0.07448 0.06661 0.0316 0.0479 1.0000 11.000 0.7895 0.07872 0.07100 0.0313 0.0480 1.0000