XFOIL Version 6.96 Calculated polar for: USA 29 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -15.500 -0.6833 0.08669 0.08468 -0.0713 1.0000 0.0183 -15.250 -0.7507 0.07478 0.07267 -0.0767 1.0000 0.0181 -15.000 -0.8135 0.06551 0.06332 -0.0797 1.0000 0.0176 -14.750 -0.9479 0.04285 0.04031 -0.1014 0.9908 0.0161 -14.500 -0.9656 0.03270 0.02981 -0.1109 0.9841 0.0163 -14.250 -0.9535 0.02834 0.02525 -0.1144 0.9807 0.0169 -14.000 -0.9348 0.02597 0.02275 -0.1158 0.9768 0.0176 -13.750 -0.9096 0.02413 0.02076 -0.1176 0.9746 0.0183 -13.500 -0.8841 0.02234 0.01881 -0.1193 0.9727 0.0193 -13.250 -0.8543 0.02128 0.01771 -0.1210 0.9714 0.0204 -13.000 -0.8213 0.02060 0.01698 -0.1228 0.9704 0.0215 -12.750 -0.7915 0.01998 0.01627 -0.1239 0.9679 0.0225 -12.500 -0.7685 0.01920 0.01541 -0.1238 0.9628 0.0235 -12.250 -0.7377 0.01879 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0.2200 0.00891 0.00220 -0.0951 0.6033 0.0588 -2.000 0.2446 0.00885 0.00210 -0.0943 0.5969 0.0620 -1.750 0.2699 0.00875 0.00201 -0.0938 0.5911 0.0680 -1.500 0.2947 0.00860 0.00196 -0.0931 0.5850 0.0953 -1.250 0.3187 0.00855 0.00192 -0.0923 0.5789 0.1139 -1.000 0.3441 0.00842 0.00187 -0.0918 0.5738 0.1323 -0.750 0.3679 0.00827 0.00184 -0.0910 0.5682 0.1747 -0.500 0.3913 0.00824 0.00184 -0.0900 0.5626 0.2005 -0.250 0.4163 0.00817 0.00183 -0.0894 0.5575 0.2190 0.000 0.4401 0.00813 0.00183 -0.0885 0.5521 0.2375 0.250 0.4629 0.00813 0.00186 -0.0875 0.5467 0.2591 0.500 0.4875 0.00809 0.00191 -0.0868 0.5419 0.2838 0.750 0.5117 0.00812 0.00197 -0.0860 0.5363 0.3031 1.000 0.5352 0.00820 0.00203 -0.0850 0.5308 0.3149 1.250 0.5607 0.00824 0.00207 -0.0845 0.5261 0.3238 1.500 0.5849 0.00830 0.00212 -0.0837 0.5206 0.3301 1.750 0.6079 0.00839 0.00219 -0.0827 0.5152 0.3359 2.000 0.6334 0.00845 0.00224 -0.0822 0.5102 0.3417 2.250 0.6570 0.00851 0.00232 -0.0813 0.5049 0.3476 2.500 0.6796 0.00863 0.00240 -0.0801 0.4996 0.3529 2.750 0.7045 0.00868 0.00246 -0.0795 0.4948 0.3568 3.000 0.7271 0.00873 0.00252 -0.0785 0.4895 0.3602 3.250 0.7477 0.00882 0.00259 -0.0769 0.4842 0.3632 3.500 0.7705 0.00886 0.00265 -0.0759 0.4797 0.3662 3.750 0.7917 0.00892 0.00271 -0.0745 0.4745 0.3689 4.000 0.8113 0.00903 0.00279 -0.0728 0.4694 0.3712 4.250 0.8337 0.00909 0.00286 -0.0717 0.4651 0.3731 4.500 0.8546 0.00912 0.00292 -0.0703 0.4601 0.3764 4.750 0.8744 0.00924 0.00304 -0.0686 0.4551 0.3792 5.000 0.8956 0.00933 0.00314 -0.0673 0.4506 0.3814 5.250 0.9170 0.00943 0.00325 -0.0661 0.4442 0.3850 5.500 0.9357 0.00959 0.00338 -0.0643 0.4367 0.3868 5.750 0.9566 0.00966 0.00348 -0.0629 0.4292 0.3901 6.000 0.9742 0.00983 0.00364 -0.0610 0.4217 0.3931 6.250 0.9956 0.00992 0.00376 -0.0598 0.4144 0.3956 6.500 1.0134 0.01011 0.00393 -0.0579 0.4061 0.3982 6.750 1.0344 0.01024 0.00407 -0.0567 0.3987 0.4008 7.000 1.0519 0.01043 0.00425 -0.0548 0.3897 0.4032 7.250 1.0706 0.01059 0.00442 -0.0531 0.3798 0.4051 7.500 1.0873 0.01082 0.00463 -0.0511 0.3663 0.4075 7.750 1.1019 0.01113 0.00489 -0.0488 0.3491 0.4096 8.000 1.1139 0.01156 0.00521 -0.0461 0.3251 0.4117 8.250 1.1182 0.01227 0.00572 -0.0421 0.2866 0.4135 8.500 1.1079 0.01360 0.00665 -0.0358 0.2204 0.4148 8.750 1.0862 0.01546 0.00805 -0.0281 0.1433 0.4156 9.000 1.0612 0.01763 0.00980 -0.0204 0.0638 0.4160 9.250 1.0548 0.01913 0.01114 -0.0158 0.0286 0.4178 9.500 1.0644 0.01990 0.01195 -0.0136 0.0241 0.4208 9.750 1.0742 0.02071 0.01279 -0.0115 0.0217 0.4234 10.000 1.0836 0.02158 0.01370 -0.0095 0.0199 0.4266 10.250 1.0953 0.02235 0.01453 -0.0078 0.0192 0.4303 10.500 1.1061 0.02322 0.01545 -0.0061 0.0183 0.4359 10.750 1.1140 0.02430 0.01660 -0.0043 0.0170 0.4440 11.000 1.1198 0.02559 0.01806 -0.0025 0.0160 0.4922 11.250 1.3005 0.02803 0.02167 -0.0394 0.0136 1.0000 11.500 1.3038 0.02961 0.02330 -0.0374 0.0132 1.0000 11.750 1.2980 0.03203 0.02582 -0.0349 0.0127 1.0000 12.000 1.2984 0.03408 0.02794 -0.0331 0.0126 1.0000 12.250 1.3061 0.03557 0.02948 -0.0319 0.0123 1.0000 12.500 1.3085 0.03761 0.03159 -0.0306 0.0121 1.0000 12.750 1.3082 0.03999 0.03406 -0.0293 0.0121 1.0000 13.000 1.3159 0.04166 0.03577 -0.0285 0.0115 1.0000 13.250 1.3174 0.04399 0.03816 -0.0276 0.0112 1.0000 13.500 1.3166 0.04663 0.04087 -0.0266 0.0110 1.0000 13.750 1.3209 0.04876 0.04304 -0.0260 0.0108 1.0000 14.000 1.3221 0.05127 0.04560 -0.0254 0.0106 1.0000 14.250 1.3198 0.05421 0.04861 -0.0247 0.0104 1.0000 14.500 1.3153 0.05741 0.05189 -0.0241 0.0103 1.0000 14.750 1.3119 0.06056 0.05511 -0.0236 0.0101 1.0000 15.000 1.2997 0.06476 0.05939 -0.0231 0.0098 1.0000 15.250 1.2946 0.06816 0.06287 -0.0227 0.0096 1.0000 15.500 1.2914 0.07137 0.06614 -0.0224 0.0096 1.0000 15.750 1.2938 0.07399 0.06882 -0.0222 0.0095 1.0000 16.000 1.2944 0.07686 0.07175 -0.0221 0.0094 1.0000 16.250 1.2958 0.07963 0.07460 -0.0220 0.0092 1.0000 16.500 1.2959 0.08256 0.07759 -0.0220 0.0091 1.0000 16.750 1.2961 0.08549 0.08058 -0.0219 0.0089 1.0000