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.
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:
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 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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:
Download or read book Exhaust emissions from a premixing prevaporizing flame tube using liquid jet A fuel written by Cecil J. Marek and published by . This book was released on 1976 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Off design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16 5 written by Bobby L. Berrier and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of a 10 Deg Conical Plug Nozzle with a Stowed Thrust Reverser at Mach Numbers from 0 to 2 0 written by Fred W. Steffen and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Performance of Convergent and Plug Nozzles at Mach Numbers from 0 to 1 97 written by Douglas E. Harrington and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cumulative Title Index to United States Public Documents 1789 1976 written by Daniel W. Lester and published by . This book was released on 1982 with total page 816 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of a 10 Conical Plug Nozzle with a Stowed Thrust Reverser at Mach Numbers from 0 to 2 0 written by Fred W. Steffen and published by . This book was released on 1970 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 200 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 Wind Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of 0 deg to determine the isolated performance of several expendable nozzle concepts for supersonic nonaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ratio, and cruciform shroud flap vectoring were investigated. The nozzle pressure ratio 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. The shortest nozzle had the best thrust-minus-drag performance at Mach numbers up to 0.95 but was approached in performance by other configurations at Mach numbers of 1.15 and 1.25. At Mach numbers above 1.25, the cruciform nozzle configuration having the same expansion ratio (2.64) as the fixed geometry nozzles had the best thrust-minus-drag performance. Ventilation of the fixed geometry divergent shrouds to the nozzle external boattail flow generally improved thrust-minus-drag performance at Mach numbers from 0.60 to 1.25, but decreased performance above a Mach number of 1.25. Re, Richard J. and Berrier, Bobby L. and Abeyounis, William K. Langley Research Center RTOP 706-17-21-05
Download or read book Performance of a 10 Conical Plug Nozzle with Various Primary Flap and Nacelle Configurations at Mach Numbers from 0 to 1 97 written by Douglas E. Harrington and published by . This book was released on 1970 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of Annular Plug and Expansion deflection Nozzles Including External Flow Effects at Transonic Mach Numbers written by Robert A. Wasko and published by . This book was released on 1968 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance Characteristics of Two Multiaxis Thrust vectoring Nozzles at Mach Numbers Up to 1 28 written by David J. Wing and published by . This book was released on 1993 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
