XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0013 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.1961 0.11869 0.11561 0.0196 1.0000 0.0154 -18.250 -1.2313 0.10736 0.10410 0.0132 1.0000 0.0154 -18.000 -1.2609 0.09746 0.09402 0.0077 1.0000 0.0154 -17.750 -1.2851 0.08875 0.08514 0.0028 1.0000 0.0154 -17.500 -1.3043 0.08118 0.07740 -0.0013 1.0000 0.0155 -17.250 -1.3193 0.07466 0.07073 -0.0048 1.0000 0.0156 -17.000 -1.3311 0.06895 0.06486 -0.0076 1.0000 0.0158 -16.750 -1.3401 0.06401 0.05978 -0.0097 1.0000 0.0160 -16.500 -1.3475 0.05963 0.05526 -0.0113 1.0000 0.0161 -16.250 -1.3530 0.05575 0.05124 -0.0125 1.0000 0.0163 -16.000 -1.3566 0.05228 0.04764 -0.0132 1.0000 0.0165 -15.750 -1.3584 0.04915 0.04437 -0.0137 1.0000 0.0168 -15.500 -1.3584 0.04634 0.04142 -0.0139 1.0000 0.0170 -15.250 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0.8154 0.0550 -5.750 -0.6557 0.01282 0.00537 0.0064 0.8114 0.0590 -5.500 -0.6279 0.01258 0.00511 0.0062 0.8072 0.0630 -5.250 -0.6005 0.01227 0.00483 0.0061 0.8031 0.0695 -5.000 -0.5729 0.01202 0.00457 0.0060 0.7996 0.0766 -4.750 -0.5449 0.01176 0.00434 0.0058 0.7961 0.0857 -4.500 -0.5169 0.01147 0.00411 0.0056 0.7923 0.0980 -4.000 -0.4611 0.01088 0.00366 0.0051 0.7849 0.1356 -3.750 -0.4332 0.01058 0.00344 0.0049 0.7817 0.1618 -3.500 -0.4051 0.01018 0.00323 0.0045 0.7781 0.2008 -3.250 -0.3772 0.00974 0.00301 0.0041 0.7746 0.2552 -3.000 -0.3492 0.00930 0.00281 0.0037 0.7711 0.3141 -2.500 -0.2926 0.00851 0.00242 0.0030 0.7647 0.4248 -2.250 -0.2648 0.00786 0.00226 0.0025 0.7613 0.5388 -2.000 -0.2361 0.00761 0.00225 0.0022 0.7578 0.6042 -1.750 -0.2068 0.00753 0.00224 0.0019 0.7544 0.6308 -1.500 -0.1775 0.00749 0.00224 0.0017 0.7512 0.6543 -1.250 -0.1482 0.00748 0.00227 0.0015 0.7483 0.6755 -1.000 -0.1185 0.00746 0.00230 0.0012 0.7438 0.6909 -0.750 -0.0887 0.00746 0.00228 0.0008 0.7384 0.7006 -0.500 -0.0595 0.00746 0.00226 0.0006 0.7334 0.7068 -0.250 -0.0295 0.00746 0.00227 0.0003 0.7279 0.7150 0.000 0.0000 0.00745 0.00228 0.0000 0.7219 0.7218 0.250 0.0295 0.00746 0.00227 -0.0003 0.7151 0.7280 0.500 0.0595 0.00746 0.00226 -0.0006 0.7068 0.7335 0.750 0.0887 0.00746 0.00228 -0.0008 0.7006 0.7384 1.000 0.1185 0.00746 0.00230 -0.0012 0.6909 0.7437 1.250 0.1482 0.00748 0.00227 -0.0015 0.6753 0.7482 1.500 0.1775 0.00749 0.00224 -0.0017 0.6545 0.7512 1.750 0.2068 0.00753 0.00224 -0.0019 0.6310 0.7544 2.000 0.2361 0.00761 0.00225 -0.0022 0.6037 0.7578 2.250 0.2648 0.00786 0.00226 -0.0025 0.5396 0.7613 2.500 0.2926 0.00851 0.00242 -0.0029 0.4252 0.7647 2.750 0.3209 0.00893 0.00262 -0.0034 0.3659 0.7678 3.000 0.3492 0.00930 0.00281 -0.0037 0.3142 0.7711 3.250 0.3772 0.00974 0.00301 -0.0041 0.2548 0.7746 3.500 0.4051 0.01018 0.00323 -0.0045 0.2010 0.7781 3.750 0.4332 0.01057 0.00344 -0.0049 0.1619 0.7817 4.000 0.4611 0.01088 0.00366 -0.0051 0.1357 0.7849 4.500 0.5169 0.01147 0.00411 -0.0056 0.0979 0.7923 4.750 0.5450 0.01176 0.00434 -0.0058 0.0856 0.7961 5.000 0.5729 0.01202 0.00457 -0.0060 0.0766 0.7996 5.250 0.6006 0.01227 0.00483 -0.0061 0.0695 0.8031 5.500 0.6279 0.01258 0.00511 -0.0063 0.0630 0.8072 5.750 0.6557 0.01282 0.00537 -0.0064 0.0590 0.8114 6.000 0.6832 0.01312 0.00566 -0.0065 0.0550 0.8154 6.250 0.7101 0.01341 0.00597 -0.0066 0.0518 0.8189 6.500 0.7371 0.01368 0.00628 -0.0066 0.0493 0.8230 6.750 0.7640 0.01400 0.00661 -0.0066 0.0469 0.8277 7.000 0.7902 0.01440 0.00700 -0.0066 0.0444 0.8320 7.250 0.8166 0.01468 0.00735 -0.0065 0.0428 0.8362 7.500 0.8429 0.01499 0.00771 -0.0064 0.0408 0.8407 7.750 0.8688 0.01537 0.00810 -0.0064 0.0389 0.8454 8.000 0.8936 0.01583 0.00858 -0.0061 0.0371 0.8500 8.250 0.9190 0.01617 0.00899 -0.0059 0.0359 0.8552 8.500 0.9442 0.01655 0.00943 -0.0057 0.0345 0.8606 8.750 0.9689 0.01694 0.00988 -0.0055 0.0331 0.8655 9.000 0.9926 0.01739 0.01036 -0.0051 0.0318 0.8711 9.250 1.0161 0.01790 0.01091 -0.0047 0.0306 0.8773 9.500 1.0394 0.01832 0.01143 -0.0042 0.0295 0.8835 9.750 1.0622 0.01878 0.01196 -0.0036 0.0285 0.8908 10.000 1.0845 0.01926 0.01250 -0.0030 0.0275 0.8980 10.250 1.1058 0.01978 0.01307 -0.0023 0.0267 0.9065 10.500 1.1250 0.02042 0.01377 -0.0013 0.0259 0.9166 10.750 1.1443 0.02096 0.01442 -0.0002 0.0252 0.9295 11.000 1.1629 0.02148 0.01505 0.0010 0.0245 0.9487 11.250 1.1845 0.02207 0.01573 0.0014 0.0238 1.0000 11.500 1.2043 0.02275 0.01647 0.0020 0.0232 1.0000 11.750 1.2226 0.02349 0.01726 0.0027 0.0226 1.0000 12.000 1.2378 0.02428 0.01809 0.0039 0.0221 1.0000 12.250 1.2500 0.02528 0.01913 0.0053 0.0215 1.0000 12.500 1.2630 0.02630 0.02023 0.0065 0.0211 1.0000 12.750 1.2768 0.02731 0.02134 0.0074 0.0207 1.0000 13.000 1.2896 0.02841 0.02254 0.0083 0.0203 1.0000 13.250 1.3016 0.02961 0.02383 0.0092 0.0199 1.0000 13.500 1.3128 0.03089 0.02520 0.0100 0.0195 1.0000 13.750 1.3235 0.03223 0.02662 0.0108 0.0191 1.0000 14.000 1.3335 0.03366 0.02813 0.0114 0.0187 1.0000 14.250 1.3421 0.03523 0.02978 0.0120 0.0183 1.0000 14.500 1.3485 0.03705 0.03167 0.0126 0.0180 1.0000 14.750 1.3517 0.03922 0.03392 0.0131 0.0177 1.0000 15.000 1.3547 0.04149 0.03631 0.0134 0.0174 1.0000 15.250 1.3583 0.04376 0.03871 0.0136 0.0172 1.0000 15.500 1.3600 0.04630 0.04139 0.0136 0.0170 1.0000 15.750 1.3601 0.04911 0.04433 0.0134 0.0168 1.0000 16.000 1.3584 0.05223 0.04759 0.0130 0.0165 1.0000 16.250 1.3548 0.05569 0.05118 0.0122 0.0163 1.0000 16.500 1.3495 0.05956 0.05519 0.0111 0.0161 1.0000 16.750 1.3425 0.06390 0.05967 0.0095 0.0159 1.0000 17.000 1.3334 0.06885 0.06476 0.0073 0.0158 1.0000 17.250 1.3217 0.07454 0.07060 0.0045 0.0156 1.0000 17.500 1.3067 0.08107 0.07729 0.0010 0.0155 1.0000 17.750 1.2878 0.08860 0.08499 -0.0031 0.0154 1.0000 18.000 1.2633 0.09737 0.09393 -0.0080 0.0154 1.0000 18.250 1.2339 0.10723 0.10397 -0.0135 0.0154 1.0000 18.500 1.1979 0.11872 0.11565 -0.0199 0.0154 1.0000