NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Effects of free-stream turbulence on boundary-layer transitionTraditional methods for the prediction of the transition location rest either on lump parameters like the momentum thickness or on N factors obtained from the approximate linear stability characteristics of the flow. These methods account for the effects of the disturbance environment by empirical correlation with observed transition locations. We have developed a highly efficient and accurate approach to stability analysis and transition simulation based on parabolized stability equations (PSE). Here we present a first application of this approach to realistic problems of practical interest. We study the effects of the turbulence level on transition and heat transfer in flows over flat plates, curved plates, and the stator blade of a gas-turbine model. We discuss the formulation of an input model for the PSE analysis in the light of the present knowledge of receptivity mechanisms. The input model is used to compute transition locations for various configurations and flow conditions. The results compare favorably with experimental data.
Document ID
19930039393
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Herbert, TH.
(Ohio State Univ. Columbus, United States)
Stuckert, G. K.
(NASA Lewis Research Center Cleveland, OH, United States)
Esfahanian, V.
(DynaFlow, Inc. Columbus, OH, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 93-0488
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A23390
Funding Number(s)
CONTRACT_GRANT: N00014-90-J-1520
CONTRACT_GRANT: AF-AFOSR-91-0262
CONTRACT_GRANT: NAS3-26602
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available