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Experimental Investigation of Subsonic Turbulent Boundary Layer Flow Over a Wall-Mounted Axisymmetric HillAn important goal for modern fluid mechanics experiments is to provide datasets which present a challenge for Computational Fluid Dynamics simulations to reproduce. Such "CFD validation experiments" should be well-characterized and well-documented, and should investigate flows which are difficult for CFD to calculate. It is also often convenient for the experiment to be challenging for CFD in some aspects while simple in others. This report is part of the continuing documentation of a series of experiments conducted to characterize the flow around an axisymmetric, modified-cosine-shaped, wall-mounted hill named "FAITH" (Fundamental Aero Investigates The Hill). Computation of this flow is easy in some ways - subsonic flow over a simple shape - while being complex in others - separated flow and boundary layer interactions. The primary set of experiments were performed on a 15.2 cm high, 45.7 cm base diameter machined aluminum model that was tested at mean speeds of 50 m/s (Reynolds Number based on height = 500,000). The ratio of model height to boundary later height was approximately 3. The flow was characterized using surface oil flow visualization, Cobra probe to determine point-wise steady and unsteady 3D velocities, Particle Image Velocimetry (PIV) to determine 3D velocities and turbulence statistics along specified planes, Pressure Sensitive Paint (PSP) to determine mean surface pressures, and Fringe Imaging Skin Friction (FISF) to determine surface skin friction magnitude and direction. A set of pathfinder experiments were also performed in a water channel on a smaller scale (5.1 cm high, 15.2 cm base diameter) sintered nylon model. The water channel test was conducted at a mean test section speed of 3 cm/s (Reynolds Number of 1500), but at the same ratio of model height to boundary layer thickness. Dye injection from both the model and an upstream rake was used to visualize the flow. This report summarizes the experimental set-up, techniques used, and data acquired. It also describes some details of the dataset that is being constructed for use by other researchers, especially the CFD community.
Document ID
20160011499
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Bell, James H. (NASA Ames Research Center Moffett Field, CA United States)
Heineck, James T. (NASA Ames Research Center Moffett Field, CA United States)
Zilliac, Gregory (NASA Ames Research Center Moffett Field, CA United States)
Mehta, Rabindra D. (NASA Ames Research Center Moffett Field, CA United States)
Long, Kurtis R. (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
September 27, 2016
Publication Date
September 26, 2016
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
ARC-E-DAA-TN34022
STO-MP-AVT-246
ARC-E-DAA-TN35029
Meeting Information
Meeting: NATO CSO AVT-246 Specialists Meeting
Location: Avila
Country: Spain
Start Date: September 26, 2016
End Date: September 28, 2016
Sponsors: North Atlantic Treaty Organization
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Peer Committee
Keywords
fluid machanics cfd validation wind tunnel

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