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Some recent advances in computational aerodynamics for helicopter applicationsThe growing application of computational aerodynamics to nonlinear helicopter problems is outlined, with particular emphasis on several recent quasi-two-dimensional examples that used the thin-layer Navier-Stokes equations and an eddy-viscosity model to approximate turbulence. Rotor blade section characteristics can now be calculated accurately over a wide range of transonic flow conditions. However, a finite-difference simulation of the complete flow field about a helicopter in forward flight is not currently feasible, despite the impressive progress that is being made in both two and three dimensions. The principal limitations are today's computer speeds and memories, algorithm and solution methods, grid generation, vortex modeling, structural and aerodynamic coupling, and a shortage of engineers who are skilled in both computational fluid dynamics and helicopter aerodynamics and dynamics.
Document ID
19860002740
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mccroskey, W. J. (NASA Ames Research Center Moffett Field, CA, United States)
Baeder, J. D. (Army Aviation and Technology Activity-AVSCOM Moffett Field, Calif., United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-86777
USAVSCOM-TR-85-A-06
NAS 1.15:86777
REPT-85345
AD-A160722
Accession Number
86N12207
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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