XFOIL Version 6.96 Calculated polar for: DSMA-523A 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9947 0.12346 0.12058 -0.0490 0.9849 0.0162 -19.500 -1.0406 0.11093 0.10787 -0.0559 0.9852 0.0162 -19.250 -1.0844 0.09929 0.09606 -0.0624 0.9854 0.0162 -19.000 -1.1223 0.08893 0.08554 -0.0681 0.9857 0.0162 -18.750 -1.1532 0.08009 0.07654 -0.0729 0.9860 0.0161 -18.500 -1.1775 0.07257 0.06887 -0.0770 0.9864 0.0161 -18.250 -1.1950 0.06637 0.06254 -0.0802 0.9867 0.0162 -18.000 -1.2078 0.06118 0.05722 -0.0827 0.9871 0.0162 -17.750 -1.2172 0.05676 0.05268 -0.0846 0.9874 0.0162 -17.500 -1.2237 0.05295 0.04876 -0.0859 0.9877 0.0163 -17.250 -1.2282 0.04963 0.04534 -0.0868 0.9880 0.0163 -17.000 -1.2302 0.04678 0.04240 -0.0873 0.9883 0.0163 -16.750 -1.2312 0.04424 0.03978 -0.0874 0.9885 0.0164 -16.500 -1.2351 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-0.1165 0.0479 0.6612 2.500 0.6674 0.01081 0.00376 -0.1163 0.0462 0.6629 2.750 0.6949 0.01099 0.00394 -0.1160 0.0443 0.6646 3.000 0.7221 0.01121 0.00414 -0.1157 0.0425 0.6664 3.250 0.7494 0.01143 0.00435 -0.1153 0.0410 0.6678 3.500 0.7770 0.01161 0.00453 -0.1150 0.0400 0.6689 3.750 0.8043 0.01181 0.00474 -0.1147 0.0389 0.6705 4.000 0.8313 0.01204 0.00496 -0.1143 0.0378 0.6727 4.250 0.8583 0.01229 0.00520 -0.1139 0.0366 0.6750 4.500 0.8853 0.01255 0.00543 -0.1135 0.0352 0.6759 4.750 0.9128 0.01274 0.00562 -0.1133 0.0345 0.6766 5.000 0.9400 0.01294 0.00583 -0.1130 0.0336 0.6772 5.250 0.9672 0.01316 0.00604 -0.1127 0.0326 0.6777 5.500 0.9941 0.01339 0.00625 -0.1123 0.0316 0.6781 5.750 1.0208 0.01366 0.00650 -0.1119 0.0306 0.6785 6.000 1.0474 0.01393 0.00679 -0.1115 0.0299 0.6788 6.250 1.0741 0.01417 0.00704 -0.1111 0.0294 0.6791 6.500 1.1006 0.01443 0.00731 -0.1107 0.0288 0.6794 6.750 1.1271 0.01468 0.00757 -0.1102 0.0281 0.6800 7.000 1.1534 0.01494 0.00784 -0.1098 0.0274 0.6807 7.250 1.1794 0.01522 0.00813 -0.1093 0.0268 0.6813 7.500 1.2051 0.01554 0.00845 -0.1087 0.0262 0.6818 7.750 1.2303 0.01592 0.00885 -0.1081 0.0255 0.6823 8.000 1.2558 0.01622 0.00919 -0.1075 0.0252 0.6829 8.250 1.2811 0.01655 0.00955 -0.1069 0.0249 0.6834 8.500 1.3062 0.01688 0.00993 -0.1062 0.0244 0.6838 8.750 1.3310 0.01724 0.01032 -0.1055 0.0240 0.6844 9.000 1.3556 0.01760 0.01071 -0.1048 0.0236 0.6850 9.250 1.3800 0.01798 0.01112 -0.1040 0.0232 0.6856 9.500 1.4041 0.01837 0.01154 -0.1032 0.0228 0.6862 9.750 1.4279 0.01878 0.01198 -0.1023 0.0225 0.6868 10.000 1.4512 0.01923 0.01246 -0.1014 0.0220 0.6873 10.250 1.4738 0.01976 0.01302 -0.1004 0.0216 0.6878 10.500 1.4963 0.02026 0.01357 -0.0993 0.0213 0.6883 10.750 1.5189 0.02071 0.01407 -0.0983 0.0211 0.6889 11.000 1.5411 0.02118 0.01461 -0.0972 0.0209 0.6894 11.250 1.5628 0.02168 0.01517 -0.0960 0.0207 0.6900 11.500 1.5840 0.02221 0.01575 -0.0948 0.0204 0.6905 11.750 1.6053 0.02269 0.01629 -0.0936 0.0201 0.6910 12.000 1.6258 0.02322 0.01688 -0.0922 0.0198 0.6916 12.250 1.6457 0.02377 0.01748 -0.0908 0.0196 0.6921 12.500 1.6650 0.02435 0.01811 -0.0893 0.0193 0.6926 12.750 1.6835 0.02496 0.01878 -0.0877 0.0191 0.6931 13.000 1.7011 0.02561 0.01948 -0.0860 0.0188 0.6937 13.250 1.7175 0.02631 0.02024 -0.0841 0.0187 0.6941 13.500 1.7328 0.02704 0.02104 -0.0820 0.0185 0.6946 13.750 1.7435 0.02780 0.02187 -0.0791 0.0183 0.6950 14.000 1.7528 0.02866 0.02281 -0.0761 0.0181 0.6954 14.250 1.7611 0.02964 0.02386 -0.0731 0.0179 0.6958 14.500 1.7681 0.03071 0.02503 -0.0699 0.0178 0.6962 14.750 1.7769 0.03166 0.02608 -0.0672 0.0177 0.6965 15.000 1.7844 0.03272 0.02723 -0.0643 0.0176 0.6968 15.250 1.7909 0.03385 0.02846 -0.0615 0.0176 0.6971 15.500 1.7964 0.03509 0.02979 -0.0586 0.0175 0.6974 15.750 1.8008 0.03643 0.03124 -0.0559 0.0174 0.6981 16.000 1.8039 0.03793 0.03286 -0.0532 0.0173 0.6989 16.250 1.8053 0.03961 0.03465 -0.0506 0.0173 0.6996 16.500 1.8053 0.04150 0.03666 -0.0482 0.0172 0.7001 16.750 1.8034 0.04365 0.03893 -0.0460 0.0171 0.7006 17.000 1.7998 0.04608 0.04149 -0.0441 0.0171 0.7011 17.250 1.7935 0.04900 0.04454 -0.0427 0.0170 0.7015 17.500 1.7843 0.05247 0.04816 -0.0418 0.0169 0.7019 17.750 1.7735 0.05653 0.05236 -0.0419 0.0169 0.7023 18.000 1.7567 0.06196 0.05797 -0.0433 0.0168 0.7026