KERNEL FUNCTION METHOD
A Steady And Oscillatory Kernel Function Method For Interfering Surfaces In Subsonic, Transonic and Supersonic Flow
This computer program was developed to provide an analysis method based on a kernel function technique which uses assumed pressure functions with unknown coefficients. With this technique, generalized forces can be calculated in unsteady flow and pressure distributions can be obtained in both steady and unsteady flow. Once the aerodynamic matrices are computed and inverted, they may be saved and used on subsequent problems at very little cost as long as Mach number, reduced frequencies, and aerodynamic geometry remain unchanged. This method should be very useful for design applications where the structural mode shapes change continually due to structural changes and payload variations but the aerodynamic parameters remain constant.
Program Size: 5,948 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
