NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Numerical Analysis of Convection/Transpiration CoolingAn innovative concept utilizing the natural porosity of refractory-composite materials and hydrogen coolant to provide CONvective and TRANspiration (CONTRAN) cooling and oxidation protection has been numerically studied for surfaces exposed to a high heat flux high temperature environment such as hypersonic vehicle engine combustor walls. A boundary layer code and a porous media finite difference code were utilized to analyze the effect of convection and transpiration cooling on surface heat flux and temperature. The boundary layer code determined that transpiration flow is able to provide blocking of the surface heat flux only if it is above a minimum level due to heat addition from combustion of the hydrogen transpirant. The porous media analysis indicated that cooling of the surface is attained with coolant flow rates that are in the same range as those required for blocking, indicating that a coupled analysis would be beneficial.
Document ID
19990100659
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Glass, David E.
(NASA Langley Research Center Hampton, VA United States)
Dilley, Arthur D.
(FDC/NYMA, Inc. Hampton, VA United States)
Kelly, H. Neale
(Analytical Services and Materials, Inc. Hampton, VA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA Paper 99-4911
Meeting Information
Meeting: Weakly Ionized Gases
Location: Norfolk, VA
Country: United States
Start Date: November 1, 1999
End Date: November 5, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: F33657-93-C-2227
Distribution Limits
Public
Copyright
Public Use Permitted.
Document Inquiry

Available Downloads

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