Automated airplane surface generation
- NASA Langley Research Center, Hampton, VA (United States)
- Computer Sciences Corp., Hampton, VA (United States)
An efficient methodology and software axe presented for defining a class of airplane configurations. A small set of engineering design parameters and grid control parameters govern the process. The general airplane configuration has wing, fuselage, vertical tall, horizontal tail, and canard components. Wing, canard, and tail surface grids axe manifested by solving a fourth-order partial differential equation subject to Dirichlet and Neumann boundary conditions. The design variables are incorporated into the boundary conditions, and the solution is expressed as a Fourier series. The fuselage is described by an algebraic function with four design parameters. The computed surface grids are suitable for a wide range of Computational Fluid Dynamics simulation and configuration optimizations. Both batch and interactive software are discussed for applying the methodology.
- OSTI ID:
- 416551
- Report Number(s):
- CONF-960489--
- Country of Publication:
- United States
- Language:
- English
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