Computational analysis of methods for reduction of induced dragThe purpose of this effort was to perform a computational flow analysis of a design concept centered around induced drag reduction and tip-vortex energy recovery. The flow model solves the unsteady three-dimensional Euler equations, discretized as a finite-volume method, utilizing a high-resolution approximate Riemann solver for cell interface flux definitions. The numerical scheme is an approximately-factored block LU implicit Newton iterative-refinement method. Multiblock domain decomposition is used to partition the field into an ordered arrangement of blocks. Three configurations are analyzed: a baseline fuselage-wing, a fuselage-wing-nacelle, and a fuselage-wing-nacelle-propfan. Aerodynamic force coefficients, propfan performance coefficients, and flowfield maps are used to qualitatively access design efficacy. Where appropriate, comparisons are made with available experimental data.
Document ID
19930041539
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Janus, J. M. (NASA Langley Research Center Hampton, VA, United States)
Chatterjee, Animesh (NASA Langley Research Center Hampton, VA, United States)
Cave, Chris (NSF, Engineering Research Center for Computational Field Simulation; Mississippi State Univ. Mississippi State, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0524
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit