XFOIL Version 6.96 Calculated polar for: NACA 0010 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.7178 0.08934 0.08227 -0.0040 1.0000 0.1846 -9.000 -0.7157 0.08339 0.07632 -0.0055 1.0000 0.1784 -8.750 -0.7856 0.06961 0.06229 -0.0150 1.0000 0.1541 -8.500 -0.7896 0.06406 0.05656 -0.0153 1.0000 0.1519 -8.250 -0.7945 0.05868 0.05086 -0.0153 1.0000 0.1510 -8.000 -0.7949 0.05380 0.04556 -0.0147 1.0000 0.1515 -7.750 -0.7903 0.04929 0.04056 -0.0138 1.0000 0.1522 -7.500 -0.7809 0.04514 0.03588 -0.0126 1.0000 0.1528 -7.250 -0.7677 0.04149 0.03163 -0.0113 1.0000 0.1545 -7.000 -0.7491 0.03874 0.02871 -0.0103 1.0000 0.1605 -6.750 -0.7299 0.03631 0.02592 -0.0091 1.0000 0.1677 -6.500 -0.7086 0.03364 0.02287 -0.0081 1.0000 0.1735 -6.250 -0.6851 0.03148 0.02050 -0.0071 1.0000 0.1825 -6.000 -0.6617 0.02956 0.01850 -0.0062 1.0000 0.1962 -5.750 -0.6388 0.02779 0.01666 -0.0051 1.0000 0.2165 -5.500 -0.6151 0.02600 0.01495 -0.0039 1.0000 0.2445 -5.250 -0.5944 0.02439 0.01364 -0.0023 1.0000 0.2904 -5.000 -0.5765 0.02294 0.01275 -0.0001 1.0000 0.3557 -4.750 -0.5611 0.02183 0.01218 0.0030 1.0000 0.4370 -4.500 -0.5458 0.02107 0.01186 0.0065 1.0000 0.5194 -4.250 -0.5289 0.02061 0.01174 0.0104 1.0000 0.5921 -4.000 -0.5113 0.02037 0.01171 0.0145 1.0000 0.6574 -3.750 -0.4921 0.02038 0.01186 0.0188 1.0000 0.7159 -3.500 -0.4692 0.02063 0.01213 0.0229 1.0000 0.7691 -3.250 -0.4369 0.02110 0.01251 0.0255 1.0000 0.8201 -3.000 -0.3860 0.02170 0.01286 0.0243 1.0000 0.8695 -2.750 -0.2973 0.02226 0.01295 0.0151 1.0000 0.9154 -2.500 -0.1955 0.02199 0.01223 0.0013 1.0000 0.9559 -2.250 -0.1029 0.02098 0.01090 -0.0124 1.0000 0.9921 -2.000 -0.0702 0.02006 0.00988 -0.0159 1.0000 1.0000 -1.750 -0.0580 0.01940 0.00918 -0.0153 1.0000 1.0000 -1.500 -0.0463 0.01884 0.00859 -0.0143 1.0000 1.0000 -1.250 -0.0354 0.01839 0.00812 -0.0129 1.0000 1.0000 -1.000 -0.0257 0.01803 0.00776 -0.0111 1.0000 1.0000 -0.750 -0.0175 0.01776 0.00750 -0.0088 1.0000 1.0000 -0.500 -0.0110 0.01757 0.00732 -0.0060 1.0000 1.0000 -0.250 -0.0053 0.01745 0.00721 -0.0031 1.0000 1.0000 0.000 0.0000 0.01742 0.00718 0.0000 1.0000 1.0000 0.250 0.0053 0.01745 0.00721 0.0031 1.0000 1.0000 0.500 0.0110 0.01757 0.00731 0.0060 1.0000 1.0000 0.750 0.0176 0.01776 0.00750 0.0088 1.0000 1.0000 1.000 0.0257 0.01803 0.00776 0.0111 1.0000 1.0000 1.250 0.0354 0.01839 0.00812 0.0129 1.0000 1.0000 1.500 0.0464 0.01884 0.00859 0.0143 1.0000 1.0000 1.750 0.0581 0.01939 0.00917 0.0153 1.0000 1.0000 2.000 0.0703 0.02006 0.00987 0.0159 1.0000 1.0000 2.250 0.1029 0.02098 0.01089 0.0124 0.9921 1.0000 2.500 0.1955 0.02199 0.01223 -0.0013 0.9559 1.0000 2.750 0.2974 0.02226 0.01294 -0.0151 0.9155 1.0000 3.000 0.3860 0.02170 0.01285 -0.0243 0.8695 1.0000 3.250 0.4369 0.02110 0.01251 -0.0255 0.8201 1.0000 3.500 0.4692 0.02063 0.01213 -0.0229 0.7692 1.0000 3.750 0.4921 0.02038 0.01186 -0.0188 0.7159 1.0000 4.000 0.5113 0.02037 0.01171 -0.0145 0.6574 1.0000 4.250 0.5289 0.02061 0.01174 -0.0104 0.5921 1.0000 4.500 0.5458 0.02107 0.01186 -0.0065 0.5194 1.0000 4.750 0.5610 0.02183 0.01218 -0.0030 0.4370 1.0000 5.000 0.5765 0.02294 0.01275 0.0001 0.3557 1.0000 5.250 0.5944 0.02439 0.01364 0.0023 0.2904 1.0000 5.500 0.6151 0.02599 0.01495 0.0039 0.2445 1.0000 5.750 0.6388 0.02779 0.01666 0.0051 0.2165 1.0000 6.000 0.6617 0.02956 0.01850 0.0062 0.1962 1.0000 6.250 0.6851 0.03148 0.02050 0.0071 0.1825 1.0000 6.500 0.7086 0.03364 0.02287 0.0081 0.1736 1.0000 6.750 0.7299 0.03630 0.02591 0.0091 0.1677 1.0000 7.000 0.7492 0.03874 0.02871 0.0103 0.1605 1.0000 7.250 0.7678 0.04149 0.03164 0.0113 0.1545 1.0000 7.500 0.7809 0.04514 0.03588 0.0126 0.1528 1.0000 7.750 0.7904 0.04929 0.04057 0.0138 0.1522 1.0000 8.000 0.7949 0.05380 0.04556 0.0147 0.1515 1.0000 8.250 0.7946 0.05869 0.05086 0.0153 0.1510 1.0000 8.500 0.7897 0.06408 0.05657 0.0153 0.1519 1.0000 8.750 0.7857 0.06963 0.06231 0.0149 0.1541 1.0000 9.000 0.7159 0.08346 0.07640 0.0054 0.1786 1.0000 9.250 0.7090 0.09293 0.08587 -0.0001 0.2011 1.0000