NDLI: Fuselage and nozzle pressure distributions of a 1/12-scale f-15 propulsion model at transonic speeds. effect of fuselage modifications and nozzle variables

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Fuselage and nozzle pressure distributions of a 1/12-scale f-15 propulsion model at transonic speeds. effect of fuselage modifications and nozzle variables

Content Provider	NASA Technical Reports Server (NTRS)
Author	Carson Jr., G. T. Pendergraft Jr., O. C.
Copyright Year	1984
Description	Static pressure coefficient distributions on the forebody, afterbody, and nozzles of a 1/12 scale F-15 propulsion model was determined in the 16 foot transonic tunnel for Mach numbers from 0.60 to 1.20, angles of attack from -2 deg to 7 deg and ratio of jet total pressure to free stream static pressure from 1 up to about 7, depending on Mach number. The effects of nozzle geometry and horizontal tail deflection on the pressure distributions were investigated. Boundary layer total pressure profiles were determined at two locations ahead of the nozzles on the top nacelle surface. Reynolds number varied from about 1.0 x 10 to the 7th power per meter, depending on Mach number.
File Size	28500953
Page Count	470
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840024284
Archival Resource Key	ark:/13960/t47q3tp3s
Language	English
Publisher Date	1984-08-01
Access Restriction	Open
Subject Keyword	Aerodynamics Nozzle Geometry Afterbodies Flow Distribution Wind Tunnel Tests Body-wing and Tail Configurations Pressure Distribution Transonic Speed Fuselages Angle of Attack Supersonic Boundary Layers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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