Turbulent Skin Friction on Axial Compressor Blading
Loading...
Authors
Walker, G.J.
Subjects
Advisors
Date of Issue
1990-07
Date
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Language
Abstract
Measurements of turbulent boundary layers in strongly-decelerating flow on axial compressor blades operating at low Reynolds numbers have indicated skin friction values differing by as much as 50% from the predictions of conventional friction laws. A new friction law incorporating strong pressure gradient and longitudinal acceleration effects in the wall layer has been found capable of describing the observed behavior.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/3.25193
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
2 p.
Citation
Walker, G. J. "Turbulent skin friction on axial compressor blading." AIAA journal 28.7 (1990): 1201-1202.
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.