Thrust Performance Of Isolated Plug Nozzles With Two Types Of 40 Spoke Noise Suppressor At Mach Numbers From 0 To 045 PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Thrust Performance Of Isolated Plug Nozzles With Two Types Of 40 Spoke Noise Suppressor At Mach Numbers From 0 To 045 PDF full book. Access full book title Thrust Performance Of Isolated Plug Nozzles With Two Types Of 40 Spoke Noise Suppressor At Mach Numbers From 0 To 045.
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1974 |
| Genre | : Airplanes |
| ISBN | : |
Download Thrust Performance of Isolated Plug Nozzles with Two Types of 40-spoke Noise Suppressor at Mach Numbers from 0 to 0.45 Book in PDF, ePub and Kindle
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.
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1976 |
| Genre | : Airplanes |
| ISBN | : |
Download Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 Book in PDF, ePub and Kindle
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 52 |
| Release | : 1975 |
| Genre | : Airplanes |
| ISBN | : |
Download Thrust Performance of Isolated 36-chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0.45 Book in PDF, ePub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 376 |
| Release | : 1976 |
| Genre | : Aeronautics |
| ISBN | : |
Download NASA Technical Memorandum Book in PDF, ePub and Kindle
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1975 |
| Genre | : |
| ISBN | : |
Download Thrust Performance of Isolated 36-chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0.45 Book in PDF, ePub and Kindle
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 35 |
| Release | : 1976 |
| Genre | : |
| ISBN | : |
Download Thrust Performance of Isolated, Two-dimensional Suppressed Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0.45 Book in PDF, ePub and Kindle
| Author | : Cecil J. Marek |
| Publisher | : |
| Total Pages | : 62 |
| Release | : 1976 |
| Genre | : Aircraft exhaust emissions |
| ISBN | : |
Download Exhaust emissions from a premixing, prevaporizing flame tube using liquid jet A fuel Book in PDF, ePub and Kindle
| Author | : Bobby L. Berrier |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1967 |
| Genre | : Nozzles |
| ISBN | : |
Download Off-design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16.5 Book in PDF, ePub and Kindle
| Author | : Fred W. Steffen |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1970 |
| Genre | : |
| ISBN | : |
Download Performance of a 10 Deg Conical Plug Nozzle with a Stowed Thrust Reverser at Mach Numbers from 0 to 2.0 Book in PDF, ePub and Kindle
| Author | : Richard J. Re |
| Publisher | : |
| Total Pages | : 202 |
| Release | : 2001 |
| Genre | : Mach number |
| ISBN | : |
Download Isolated Performance at Mach Numbers From 0.60 to 2.86 of Several Expendable Nozzle Concepts for Supersonic Applications Book in PDF, ePub and Kindle
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.
