Add to ORKGA cooled-gas pyrometer designed for application in a hypersonic research engine program was fabricated and tested. Design and operational considerations and calibration data are presented. The probe was tested in a rocket-engine exhaust stream operating at Mach 2 and 2300 K. Test temperature measurements agreed to within 2 percent with a radiation shielded thermocouple probe
Shock tunnels or hot shot facilities are used for the simulation of re-entry conditions in aerodynam...
The work described is part of a program (Englund and Seasholtz, 1988) to develop sensors and sensing...
The capabilities of a heated tube facility used for testing rocket engine coolant channels at the NA...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
Total temperature measurement in exhaust stream of air breathing engines like Ramjet, Scramjet and A...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
A turbine blade temperature measuring system for liquid oxygen turbopumps is reported. The system in...
The development of an advanced measuring system which measures the rapidly varying gas temperature a...
A high resolution pyrometer was developed and used to obtain temperature profiles of rotating turbin...
Internal gas temperature is one of the most fundamental parameters related to engine efficiency and ...
A major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the develo...
A multiwavelength pyrometer possessing advantages over the one- and two-wavelength designs is descri...
Thin film, heat flux probe for measuring gas velocities in unstable rocket combusto
A high-resolution pyrometer was developed and tested on a modified turbine engine. The pyrometer was...
Shock tunnels or hot shot facilities are used for the simulation of re-entry conditions in aerodynam...
The work described is part of a program (Englund and Seasholtz, 1988) to develop sensors and sensing...
The capabilities of a heated tube facility used for testing rocket engine coolant channels at the NA...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
Total temperature measurement in exhaust stream of air breathing engines like Ramjet, Scramjet and A...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
A turbine blade temperature measuring system for liquid oxygen turbopumps is reported. The system in...
The development of an advanced measuring system which measures the rapidly varying gas temperature a...
A high resolution pyrometer was developed and used to obtain temperature profiles of rotating turbin...
Internal gas temperature is one of the most fundamental parameters related to engine efficiency and ...
A major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the develo...
A multiwavelength pyrometer possessing advantages over the one- and two-wavelength designs is descri...
Thin film, heat flux probe for measuring gas velocities in unstable rocket combusto
A high-resolution pyrometer was developed and tested on a modified turbine engine. The pyrometer was...
Shock tunnels or hot shot facilities are used for the simulation of re-entry conditions in aerodynam...
The work described is part of a program (Englund and Seasholtz, 1988) to develop sensors and sensing...
The capabilities of a heated tube facility used for testing rocket engine coolant channels at the NA...