A direct method to calculate disturbance fields of moving bodies at subsonic speeds in compressible media
Abstract
A panel method for the analysis of three-dimensional steady compressible subsonic flow was developed. It is based on a first order panel method, into which Mach-number dependent aerodynamic influence coefficients are incorporated. The procedure using linearized theory takes into account the real magnitudes of potentials and velocities that are induced by disturbance sources at a point in space and which in compressible flow differ from that in incompressible flow. In this way it is possible to apply the exact boundary condition directly at the original body surface. Comparisons of solutions obtained by this method with measurements and with the results from methods solving full potential equation show good agreement for subcritical Mach numbers.
- Publication:
-
Ph.D. Thesis
- Pub Date:
- April 1985
- Bibcode:
- 1985PhDT........34K
- Keywords:
-
- Compressible Flow;
- Panel Method (Fluid Dynamics);
- Perturbation;
- Subsonic Flow;
- Aerodynamic Coefficients;
- Linearization;
- Mach Number;
- Potential Theory;
- Three Dimensional Flow;
- Fluid Mechanics and Heat Transfer