Integration of the supersonic kernel function
Abstract
Integrals resulting from a zero-order discontinuous pressure distribution can be arranged in such a way that they can be solved by either normal quadrature or curve fitting followed by analytical integration. This ability simplifies the panel method for unsteady supersonic flow and is essential to model the discontinuities that occur in reality, e.g., at supersonic leading or trailing edges and control surface hinge lines.
- Publication:
-
Journal of Aircraft
- Pub Date:
- November 1994
- Bibcode:
- 1994JAir...31.1433V
- Keywords:
-
- Integrals;
- Kernel Functions;
- Panel Method (Fluid Dynamics);
- Supersonic Flow;
- Unsteady Flow;
- Curve Fitting;
- Discontinuity;
- Hinges;
- Leading Edges;
- Pressure Distribution;
- Quadratures;
- Trailing Edges;
- Fluid Mechanics and Heat Transfer