A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Research Center (UTRC) Acoustic Research Tunnel, an ultra-low freestream turbulence facility capable of laminar boundary layer research. Boundary layer computational fluid dynamics and stability modeling were used to provide pre-test predictions, as well as to aid in interpretation of measured results. Measurements were carried out at chord Reynolds numbers 2–3 × 106, with the model set at multiple incidence angles to establish a range of relevant leading edge pressure gradients. The combination of pressure gradient and flight Reynolds number testing on a thin airfoil has produced a unique data set relevant to propulsion system turbomachinery.
Skip Nav Destination
Sign In or Register for Account
ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
June 11–15, 2018
Oslo, Norway
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5099-2
PROCEEDINGS PAPER
Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow
Brian M. Holley
,
Brian M. Holley
United Technologies Research Center, East Hartford, CT
Search for other works by this author on:
Larry W. Hardin
,
Larry W. Hardin
United Technologies Research Center, East Hartford, CT
Search for other works by this author on:
Gregory Tillman
,
Gregory Tillman
United Technologies Research Center, East Hartford, CT
Search for other works by this author on:
Ray-Sing Lin
,
Ray-Sing Lin
United Technologies Research Center, East Hartford, CT
Search for other works by this author on:
Jongwook Joo
Jongwook Joo
United Technologies Research Center, East Hartford, CT
Search for other works by this author on:
Brian M. Holley
United Technologies Research Center, East Hartford, CT
Larry W. Hardin
United Technologies Research Center, East Hartford, CT
Gregory Tillman
United Technologies Research Center, East Hartford, CT
Ray-Sing Lin
United Technologies Research Center, East Hartford, CT
Jongwook Joo
United Technologies Research Center, East Hartford, CT
Paper No:
GT2018-76708, V02AT39A037; 16 pages
Published Online:
August 30, 2018
Citation
Holley, BM, Hardin, LW, Tillman, G, Lin, R, & Joo, J. "Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 2A: Turbomachinery. Oslo, Norway. June 11–15, 2018. V02AT39A037. ASME. https://doi.org/10.1115/GT2018-76708
Download citation file:
Sign In
31
Views
0
Citations
Related Proceedings Papers
Related Articles
Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow
J. Turbomach (February,2020)
Development of a Large-Scale Wind Tunnel for the Simulation of Turbomachinery Airfoil Boundary Layers
J. Eng. Power (October,1981)
Related Chapters
Introduction
Design and Analysis of Centrifugal Compressors
Hydraulic Resistance
Heat Transfer & Hydraulic Resistance at Supercritical Pressures in Power Engineering Applications
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)