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Extension of a three-dimensional viscous wing flow analysisThree-dimensional unsteady viscous effects can significantly influence the performance of fixed and rotary wing aircraft. These effects are important in both flows about helicopter rotors in forward flight and flows about 3-D (swept and tapered) supercritical wings. A computational procedure for calculating such flow field is developed, and therefore would be of great value in the design process as well as in understanding the corresponding flow phenomena. The procedure is based upon an alternating direction technique employing the Linearized Block Implicit method for solving 3-D viscous flow problems. In order to demonstrate the viability of this method, 2-D and 3-D problems are computed. These include the flow over a 2-D NACA 0012 airfoil under steady and oscillating conditions, and the steady, skewed, 3-D flow on a flat plate. Although actual 3-D flows over wings were not obtained, the ground work was laid for considering such flows. The description of the computational procedure and results are given.
Document ID
19900014032
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Weinberg, Bernard C. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Chen, Shyi-Yaung (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Thoren, Stephen J. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Shamroth, Stephen J. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-182023
SRA-900049F
NAS 1.26:182023
Accession Number
90N23348
Funding Number(s)
CONTRACT_GRANT: NAS1-18140
PROJECT: RTOP 505-63-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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