XFOIL Version 6.96 Calculated polar for: S1010 HPV airfoil 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.7647 0.08244 0.07907 0.0049 1.0000 0.0110 -10.000 -0.7870 0.07326 0.06996 -0.0012 1.0000 0.0108 -9.500 -0.8461 0.05123 0.04767 -0.0159 1.0000 0.0100 -9.250 -0.8638 0.04387 0.03985 -0.0169 1.0000 0.0100 -9.000 -0.8693 0.03803 0.03343 -0.0164 1.0000 0.0101 -8.750 -0.8651 0.03347 0.02828 -0.0153 1.0000 0.0105 -8.500 -0.8536 0.03011 0.02440 -0.0141 1.0000 0.0110 -8.250 -0.8385 0.02734 0.02118 -0.0130 1.0000 0.0115 -8.000 -0.8211 0.02546 0.01910 -0.0122 1.0000 0.0129 -7.750 -0.7994 0.02453 0.01802 -0.0116 1.0000 0.0145 -7.500 -0.7783 0.02302 0.01621 -0.0108 1.0000 0.0162 -7.250 -0.7565 0.02153 0.01440 -0.0098 1.0000 0.0174 -7.000 -0.7364 0.01972 0.01243 -0.0089 1.0000 0.0195 -6.750 -0.7126 0.01910 0.01167 -0.0083 1.0000 0.0225 -6.500 -0.6890 0.01821 0.01059 -0.0076 1.0000 0.0250 -6.250 -0.6662 0.01712 0.00934 -0.0067 1.0000 0.0269 -6.000 -0.6430 0.01627 0.00844 -0.0059 1.0000 0.0308 -5.750 -0.6189 0.01564 0.00770 -0.0052 1.0000 0.0354 -5.500 -0.5955 0.01485 0.00684 -0.0044 1.0000 0.0403 -5.250 -0.5714 0.01429 0.00622 -0.0037 1.0000 0.0475 -5.000 -0.5474 0.01375 0.00563 -0.0030 1.0000 0.0558 -4.750 -0.5231 0.01332 0.00516 -0.0023 1.0000 0.0647 -4.500 -0.4988 0.01295 0.00480 -0.0016 1.0000 0.0766 -4.250 -0.4747 0.01260 0.00448 -0.0009 1.0000 0.0906 -4.000 -0.4507 0.01226 0.00416 -0.0002 1.0000 0.1036 -3.750 -0.4268 0.01193 0.00384 0.0006 1.0000 0.1169 -3.500 -0.4030 0.01162 0.00354 0.0014 1.0000 0.1299 -3.250 -0.3793 0.01132 0.00324 0.0022 1.0000 0.1443 -3.000 -0.3557 0.01102 0.00301 0.0030 1.0000 0.1633 -2.750 -0.3323 0.01073 0.00280 0.0039 1.0000 0.1861 -2.500 -0.3090 0.01044 0.00261 0.0047 1.0000 0.2131 -2.250 -0.2861 0.01012 0.00245 0.0056 1.0000 0.2508 -2.000 -0.2637 0.00975 0.00229 0.0065 1.0000 0.3027 -1.750 -0.2421 0.00931 0.00217 0.0076 1.0000 0.3789 -1.500 -0.2219 0.00875 0.00207 0.0089 1.0000 0.4897 -1.250 -0.2053 0.00803 0.00208 0.0113 1.0000 0.6531 -1.000 -0.1884 0.00770 0.00225 0.0142 1.0000 0.7959 -0.750 -0.1653 0.00766 0.00237 0.0158 1.0000 0.8636 -0.500 -0.1048 0.00770 0.00246 0.0095 0.9850 0.9129 -0.250 -0.0475 0.00771 0.00247 0.0038 0.9700 0.9382 0.000 0.0000 0.00771 0.00247 0.0000 0.9559 0.9559 0.250 0.0476 0.00771 0.00247 -0.0038 0.9381 0.9700 0.500 0.1048 0.00770 0.00246 -0.0095 0.9130 0.9851 0.750 0.1651 0.00766 0.00237 -0.0157 0.8639 1.0000 1.000 0.1882 0.00770 0.00224 -0.0142 0.7951 1.0000 1.250 0.2052 0.00803 0.00208 -0.0112 0.6532 1.0000 1.500 0.2218 0.00875 0.00207 -0.0089 0.4901 1.0000 1.750 0.2419 0.00931 0.00216 -0.0075 0.3798 1.0000 2.000 0.2635 0.00975 0.00228 -0.0065 0.3030 1.0000 2.250 0.2859 0.01012 0.00245 -0.0055 0.2508 1.0000 2.500 0.3088 0.01044 0.00261 -0.0047 0.2133 1.0000 2.750 0.3320 0.01073 0.00280 -0.0038 0.1862 1.0000 3.000 0.3555 0.01102 0.00301 -0.0030 0.1634 1.0000 3.250 0.3790 0.01132 0.00324 -0.0022 0.1443 1.0000 3.500 0.4027 0.01162 0.00354 -0.0014 0.1300 1.0000 3.750 0.4266 0.01193 0.00384 -0.0006 0.1169 1.0000 4.000 0.4505 0.01226 0.00415 0.0002 0.1037 1.0000 4.250 0.4745 0.01260 0.00448 0.0009 0.0907 1.0000 4.500 0.4987 0.01295 0.00479 0.0016 0.0766 1.0000 4.750 0.5229 0.01332 0.00516 0.0023 0.0649 1.0000 5.000 0.5472 0.01375 0.00563 0.0030 0.0559 1.0000 5.250 0.5713 0.01429 0.00622 0.0037 0.0475 1.0000 5.500 0.5954 0.01485 0.00684 0.0044 0.0403 1.0000 5.750 0.6189 0.01564 0.00770 0.0052 0.0354 1.0000 6.000 0.6430 0.01626 0.00843 0.0059 0.0308 1.0000 6.250 0.6662 0.01713 0.00935 0.0067 0.0269 1.0000 6.500 0.6891 0.01822 0.01059 0.0075 0.0250 1.0000 6.750 0.7127 0.01911 0.01167 0.0083 0.0225 1.0000 7.000 0.7366 0.01971 0.01242 0.0088 0.0195 1.0000 7.250 0.7567 0.02154 0.01441 0.0098 0.0174 1.0000 7.500 0.7786 0.02302 0.01622 0.0107 0.0162 1.0000 7.750 0.7997 0.02459 0.01809 0.0116 0.0145 1.0000 8.000 0.8219 0.02528 0.01888 0.0120 0.0127 1.0000 8.250 0.8390 0.02735 0.02118 0.0129 0.0115 1.0000 8.500 0.8541 0.03014 0.02443 0.0140 0.0110 1.0000 8.750 0.8655 0.03354 0.02836 0.0152 0.0105 1.0000 9.000 0.8699 0.03805 0.03345 0.0162 0.0102 1.0000 9.250 0.8641 0.04398 0.03996 0.0167 0.0100 1.0000 9.500 0.8472 0.05120 0.04764 0.0158 0.0101 1.0000 10.000 0.7888 0.07315 0.06986 0.0010 0.0108 1.0000 10.250 0.7661 0.08246 0.07909 -0.0052 0.0110 1.0000