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Rapid Airplane Parametric Input Design(RAPID)An efficient methodology is presented for defining a class of airplane configurations. Inclusive in this definition are surface grids, volume grids, and grid sensitivity. A small set of design parameters and grid control parameters govern the process. The general airplane configuration has wing, fuselage, vertical tail, horizontal tail, and canard components. The wing, tail, and canard components are 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 has circular cross section, and the radius is an algebraic function of four design parameters and an independent computational variable. Volume grids are obtained through an application of the Control Point Form method. Grid sensitivity is obtained by applying the automatic differentiation precompiler ADIFOR to software for the grid generation. The computed surface grids, volume grids, and sensitivity derivatives are suitable for a wide range of Computational Fluid Dynamics simulation and configuration optimizations.
Document ID
Document Type
Smith, Robert E.
(NASA Langley Research Center Hampton, VA, United States)
Bloor, Malcolm I. G.
(Leeds Univ. United Kingdom)
Wilson, Michael J.
(Leeds Univ. United Kingdom)
Thomas, Almuttil M.
(Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2004
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 95-1687
Distribution Limits
Public Use Permitted.
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