Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 30
Book Description
Experimental Investigation in an Altitude Test Facility of Burning of Excess Combustibles in a Rocket Engine Exhaust
Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 30
Book Description
Some Experimental Tests to Change the Total Volume And/or Molecular Weight of Rocket Engine Exhaust Gas in an Altitude Test Facility
Author: A. J. Zazzi
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 360
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 360
Book Description
Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket - Engine Exhaust Nozzles
Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 66
Book Description
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 66
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1006
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1006
Book Description
Experimental Investigation of Close-range Rocket-exhaust Impingement on Surfaces in a Vacuum
Author: Leonard V. Clark
Publisher:
ISBN:
Category : Aircraft exhaust emissions
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aircraft exhaust emissions
Languages : en
Pages : 36
Book Description
36th Aerospace Sciences Meeting & Exhibit
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 474
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 474
Book Description
Monthly Catalog of United States Government Publications
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1812
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1812
Book Description
AIAA/ASME/SAE/ASEE 24th Joint Propulsion Conference
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 426
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 426
Book Description
National Altitude Rocket Test Facilities
Author: J. A. Suddreth
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
The necessity for experimental verification of rocket-engine performance at altitude or near-space conditions has long been recognized in the aerospace industry. Recent spacecraft rocket-engine research and development trends toward higher area ratios, advanced nozzle concepts, and nonequilibrium flow conside ations have made altitude simulation a requirement of development pro- grams. Recause the need for information regarding the capabilities and char- acteristics of altitude test facilities that are suitable for l%id-rocket%- engine operation was recognized, this survey was compiled with the help of representatives of industry and government agencies;% % INTROPUCTION The advent of upper-stage and spacecraft engine-vehicle development pro- grams along with the need for more rigorous performance and reliability data justified the construction of a number of altitude test facilities. The test capabilities of these facilities range from small attitude-control engines to large upper-stage engines. The altitude-simulating systems include simple diffusers coupled to the engine nozzle exit (fig. 1), steam ejector coupled to the engine-driven diffuser (fig. 2), and pumped environmental chambers coupled to a diffuser or ejector system for use during engine firing (fig. 3). Several techniques for vacuum generation exist. In addition to the conventional sys- tems of mechanical pumps and steam boilers for stem% ejectors, there are semi- portable liquid-propellant-driven steam generators.
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
The necessity for experimental verification of rocket-engine performance at altitude or near-space conditions has long been recognized in the aerospace industry. Recent spacecraft rocket-engine research and development trends toward higher area ratios, advanced nozzle concepts, and nonequilibrium flow conside ations have made altitude simulation a requirement of development pro- grams. Recause the need for information regarding the capabilities and char- acteristics of altitude test facilities that are suitable for l%id-rocket%- engine operation was recognized, this survey was compiled with the help of representatives of industry and government agencies;% % INTROPUCTION The advent of upper-stage and spacecraft engine-vehicle development pro- grams along with the need for more rigorous performance and reliability data justified the construction of a number of altitude test facilities. The test capabilities of these facilities range from small attitude-control engines to large upper-stage engines. The altitude-simulating systems include simple diffusers coupled to the engine nozzle exit (fig. 1), steam ejector coupled to the engine-driven diffuser (fig. 2), and pumped environmental chambers coupled to a diffuser or ejector system for use during engine firing (fig. 3). Several techniques for vacuum generation exist. In addition to the conventional sys- tems of mechanical pumps and steam boilers for stem% ejectors, there are semi- portable liquid-propellant-driven steam generators.