National Technical Reports Library

The National Technical Information Service acquires, indexes, abstracts, and archives the largest collection of U.S. government-sponsored technical reports in existence. The NTRL offers online, free and open access to these authenticated government technical reports. Technical reports and documents in its repository may be available online for free either from the issuing federal agency, the U.S. Government Publishing Office’s Federal Digital System website, or through search engines.

Details

Liquid Injection into a Supersonic Stream.

AD741887

Publication Date	1972
Personal Author	Yates, C. L.
Page Count	112
Abstract	Photographic data were obtained for the transverse injection of water and isopropyl alcohol from a flat-plate into airstreams having Mach numbers of 1.62 and 2.72. Jet/freestream dynamic pressure ratio, jet Reynolds and Weber numbers, and freestream Reynolds number were varied. Improved empirical equations for jet penetration and width were developed and substantiated for two sets of test conditions by detailed flowfield mapping 50 jet diameters downstream using pitot-pressure, cone-static-pressure, and heated sampling probes. An improved theoretical analysis was obtained. (Author)
Keywords	Liquid jets Supersonic combustion ramjet engines Supersonic characteristics Fuel injection Jet mixing flow Flat plate models Flow fields Flow visualization Water injection Alcohols Wind tunnel models Equations of motion
Source Agency	Invalid Source Agency Code
NTIS Subject Category	81A - Combustion & Ignition
Corporate Authors	Air Force AERO Propulsion Lab Wright-Patterson AFB Ohio
Document Type	Technical Report
Title Note	Final rept. Jan 70-Sep 71.
NTIS Issue Number	197213

Liquid Injection into a Supersonic Stream.

Liquid Injection into a Supersonic Stream.
AD741887

Publication Date	1972
Personal Author	Yates, C. L.
Page Count	112
Abstract	Photographic data were obtained for the transverse injection of water and isopropyl alcohol from a flat-plate into airstreams having Mach numbers of 1.62 and 2.72. Jet/freestream dynamic pressure ratio, jet Reynolds and Weber numbers, and freestream Reynolds number were varied. Improved empirical equations for jet penetration and width were developed and substantiated for two sets of test conditions by detailed flowfield mapping 50 jet diameters downstream using pitot-pressure, cone-static-pressure, and heated sampling probes. An improved theoretical analysis was obtained. (Author)
Keywords	Liquid jets Supersonic combustion ramjet engines Supersonic characteristics Fuel injection Jet mixing flow Flat plate models Flow fields Flow visualization Water injection Alcohols Wind tunnel models Equations of motion
Source Agency	Invalid Source Agency Code
NTIS Subject Category	81A - Combustion & Ignition
Corporate Authors	Air Force AERO Propulsion Lab Wright-Patterson AFB Ohio
Document Type	Technical Report
Title Note	Final rept. Jan 70-Sep 71.
NTIS Issue Number	197213