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Viscous-inviscid interaction method including wake effects for three-dimensional wing-body configurationsA viscous-inviscid interaction method has been developed by using a three-dimensional integral boundary-layer method which produces results in good agreement with a finite-difference method in a fraction of the computer time. The integral method is stable and robust and incorporates a model for computation in a small region of streamwise separation. A locally two-dimensional wake model, accounting for thickness and curvature effects, is also included in the interaction procedure. Computation time spent in converging an interacted result is, many times, only slightly greater than that required to converge an inviscid calculation. Results are shown from the interaction method, run at experimental angle of attack, Reynolds number, and Mach number, on a wing-body test case for which viscous effects are large. Agreement with experiment is good; in particular, the present wake model improves prediction of the spanwise lift distribution and lower surface cove pressure.
Document ID
19840019614
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Streett, C. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:1910
AIAA PAPER 81-1266
L-14053
NASA-TP-1910
Meeting Information
Meeting: AIAA 14th Fluid and Plasma Dyn. Conf.
Location: Palo Alto, CA
Country: United States
Start Date: June 22, 1981
End Date: June 24, 1981
Accession Number
84N27682
Funding Number(s)
PROJECT: RTOP 505-31-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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