VLMpc Manual - the AOE home page

D-60 Applied Computational Aerodynamicsinduced drag,leading edge thrust , suction coefficient characteristicscomputed at the desired cl from a near field solutionsection coefficientsl.e. sweepstation 2y/b angle cdii c/2b ct c/2b cs c/2b1 -0.96154 39.96069 0.00412 0.00085 0.001112 -0.88462 39.96069 0.00182 0.00507 0.006613 -0.81158 39.96069 0.00042 0.00821 0.010714 -0.73855 39.96069 0.00101 0.00912 0.011905 -0.66163 39.96069 0.00187 0.00962 0.012556 -0.58470 39.96069 0.00286 0.00985 0.012857 -0.51933 39.96069 0.00392 0.00978 0.012768 -0.45395 39.96069 0.00499 0.00967 0.012619 -0.38844 39.96069 0.00581 0.00975 0.0127210 -0.33839 39.96069 0.00675 0.00940 0.0122611 -0.27694 39.96069 0.00795 0.00872 0.0113812 -0.21924 39.96069 0.00884 0.00813 0.0138913 -0.18851 73.89906 0.00974 0.00733 0.0200214 -0.13855 73.89906 0.01161 0.00557 0.0200915 -0.05004 73.89906 0.02071 -0.00342 -0.01233contribution of the second planform to the chord or drag force16 -0.74888 37.91007 0.00645 0.00292 0.0037017 -0.69262 37.91007 0.00477 0.00715 0.0090618 -0.63637 37.91007 0.00430 0.00984 0.0124719 -0.58011 37.91007 0.00588 0.00953 0.0120820 -0.52220 37.91007 0.00755 0.00832 0.0105421 -0.46428 37.91007 0.00901 0.00640 0.0081222 -0.39877 37.91007 0.00956 0.00324 0.0040023 -0.33839 0.00000 0.00665 0.00124 0.0012824 -0.27694 0.00000 0.00449 0.00034 0.0003425 -0.21924 0.00000 0.00408 0.00003 0.0000326 -0.18851 0.00000 0.00389 -0.00001 -0.0000127 -0.13855 0.00000 0.00361 0.00002 0.0000228 -0.05004 0.00000 0.00331 0.00022 0.00022total coefficients1cdii/cl**2= 0.15439 ct= 0.04177 cs= 0.05673end of file encountered after configuration 23.Friday, November 17, 1995