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Book Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0 45

Download or read book Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1976 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Thrust Performance of Isolated Two dimensional Suppressed Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0 45

Download or read book Thrust Performance of Isolated Two dimensional Suppressed Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1976 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Technical Memorandum

Download or read book NASA Technical Memorandum written by and published by . This book was released on 1976 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Thrust Performance of Isolated 36 chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0 45

Download or read book Thrust Performance of Isolated 36 chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1975 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Thrust Performance of Isolated Plug Nozzles with Two Types of 40 spoke Noise Suppressor at Mach Numbers from 0 to 0 45

Download or read book Thrust Performance of Isolated Plug Nozzles with Two Types of 40 spoke Noise Suppressor at Mach Numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.

Book Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1976 with total page 1004 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Book International Journal of Turbo Jet engines

Download or read book International Journal of Turbo Jet engines written by and published by . This book was released on 1994 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Isolated Performance at Mach Numbers From 0 60 to 2 86 of Several Expendable Nozzle Concepts for Supersonic Applications

Download or read book Isolated Performance at Mach Numbers From 0 60 to 2 86 of Several Expendable Nozzle Concepts for Supersonic Applications written by Richard J. Re and published by . This book was released on 2001 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.

Book Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles

Download or read book Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles written by Donald P. Hearth and published by . This book was released on 1956 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height relative to the boundary-layer thickness. The pressure recovery increased at about the same rate as theoretically predicted for an inlet in a boundary layer having a one-seventh power profile, but was only about 0.68 to 0.75 of the theoretically obtainable values. Under some operating conditions, flow from the primary jet was exhausted through the auxiliary inlet. This phenomenon could be predicted from the ejector pumping characteristics.

Book Summary of Research on Jet Exit Installations

Download or read book Summary of Research on Jet Exit Installations written by and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: