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Low Velocity Difference Thermal Shear Layer Mixing Rate MeasurementsCurrent CFD modeling techniques are known to do a poor job of predicting the mixing rate and persistence of slot film flow in co-annular flowing ducts with relatively small velocity differences but large thermal gradients. A co-annular test was devised to empirically determine the mixing rate of slot film flow in a constant area circular duct (D approx. 1ft, L approx. 10ft). The axial rate of wall heat-up is a sensitive measure of the mixing rate of the two flows. The inflow conditions were varied to simulate a variety of conditions characteristic of moderate by-pass ratio engines. A series of air temperature measurements near the duct wall provided a straightforward means to measure the axial temperature distribution and thus infer the mixing rate. This data provides a characterization of the slot film mixing rates encountered in typical jet engine environments. The experimental geometry and entrance conditions, along with the sensitivity of the results as the entrance conditions vary, make this a good test for turbulence models in a regime important to modern air-breathing propulsion research and development.
Document ID
20130010719
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Bush, Robert H.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Culver, Harry C. M.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Weissbein, Dave
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Georgiadis, Nicholas J.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 27, 2013
Publication Date
January 7, 2013
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2013-1074
Meeting Information
Meeting: 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Location: Grapevine, TX
Country: United States
Start Date: January 7, 2013
End Date: January 10, 2013
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 794072.02.03.02.01
Distribution Limits
Public
Copyright
Other

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