NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
A transonic interactive boundary-layer theory for laminar and turbulent flow over swept wingsA 3-D laminar and turbulent boundary-layer method is developed for compressible flow over swept wings. The governing equations and curvature terms are derived in detail for a nonorthogonal, curvilinear coordinate system. Reynolds shear-stress terms are modeled by the Cebeci-Smith eddy-viscosity formulation. The governing equations are descretized using the second-order accurate, predictor-corrector finite-difference technique of Matsuno, which has the advantage that the crossflow difference formulas are formed independent of the sign of the crossflow velocity component. The method is coupled with a full potential wing/body inviscid code (FLO-30) and the inviscid-viscous interaction is performed by updating the original wing surface with the viscous displacement surface calculated by the boundary-layer code. The number of these global iterations ranged from five to twelve depending on Mach number, sweep angle, and angle of attack. Several test cases are computed by this method and the results are compared with another inviscid-viscous interaction method (TAWFIVE) and with experimental data.
Document ID
19890000658
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Woodson, Shawn H. (North Carolina State Univ. Raleigh, NC, United States)
Dejarnette, Fred R. (North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:4185
NASA-CR-4185
Accession Number
89N10029
Funding Number(s)
CONTRACT_GRANT: NCC1-22
PROJECT: RTOP 505-60-21-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available