Propulsion Airframe Integration Test Techniques for Hypersonic Airbreathing Configurations at NASA Langley Research Center (Invited)

Content Provider	Semantic Scholar
Author	Witte, David W. Huebner, Lawrence D. Trexler, Carl A. Cabell, Karen F. Andrews, Earl H.
Copyright Year	2003
Abstract	ABSTRACT The scope and significance of propulsion airframe integration (PAI) for hypersonic airbreathing vehicles is presented through a discussion of the PAI test techniques utilized at NASA Langley Research Center. Four primary types of PAI model tests utilized at NASA Langley for hypersonic airbreathing vehicles are discussed. The four types of PAI test models examined are the forebody/inlet test model, the partial-width/truncated propulsion flowpath test model, the powered exhaust simulation test model, and the full-length/width propulsion flowpath test model. The test technique for each of these four types of PAI test models is described, and the relevant PAI issues addressed by each test technique are illustrated through the presentation of recent PAI test data. Nomenclature AF axial force ATE aftbody trailing edge C A axial force coefficient C D drag coefficient C L lift coefficient C M pitch moment coefficient C N normal force coefficient C P pressure coefficient NF normal force M Mach number P static pressure PM pitch moment q dynamic pressure SNPR static nozzle pressure ratio Xaft axial distance from CTE α, ΑΟΑ angle of attack γ ratio of specific heats
File Format	PDF HTM / HTML
DOI	10.2514/6.2003-4406
Alternate Webpage(s)	https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040000798.pdf
Alternate Webpage(s)	http://techreports.larc.nasa.gov/ltrs/PDF/2003/aiaa/NASA-aiaa-2003-4406.pdf
Alternate Webpage(s)	http://www.cs.odu.edu/~mln/ltrs-pdfs/NASA-aiaa-2003-4406.pdf
Alternate Webpage(s)	https://www.cs.odu.edu/~mln/ltrs-pdfs/NASA-aiaa-2003-4406.pdf
Alternate Webpage(s)	https://doi.org/10.2514/6.2003-4406
Language	English
Access Restriction	Open
Content Type	Text
Resource Type	Article