Experimental data obtained from three shielded and three unshielded thermocouple probes are presented. Data taken in air at room temperature over the ranges 0.2 to 2.2 Mach number and 0.2 to 2.2 atmospheres total pressure show reproducible systematic variations of recovery with Mach number, ambient pressure, flow angle, and probe design. Time-constant data determined at Mach 0.2 and room temperature and pressure indicate that unshielded probes are several times faster in response to temperature changes than shielded probes
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspe...
This report shows how the actual performance of an airplane varies with air temperature when the pre...
The aerodynamic environment in the test section of a hypersonic shock tunnel is very hostile as the ...
This report presents the recovery characteristics of13; thermocouple temperature probes having three...
This report presents the recovery characteristics of13; thermocouple temperature probes having three...
Performance characteristics were experimentally determined for several sizes of a shielded and unshi...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
To acquire heat transfer measurements of a high temperature Mach two flow a water-cooled calorimeter...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in ...
The design and construction of an altitude chamber, in which both pressure and temperature can be va...
An experimental temperature probe package containing a fluidic oscillator temperature probe and a sh...
A total temperature probe based on the recovery temperature of a circular cylinder is described whic...
Measuring of the total temperatures of the flowing medium is one of the pivotal points in the develo...
Local heat-transfer rates on the surface of a heated flat plate at zero incidence to an air stream f...
A new total temperature measurement correction is developed for the single-shielded type of probe. T...
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspe...
This report shows how the actual performance of an airplane varies with air temperature when the pre...
The aerodynamic environment in the test section of a hypersonic shock tunnel is very hostile as the ...
This report presents the recovery characteristics of13; thermocouple temperature probes having three...
This report presents the recovery characteristics of13; thermocouple temperature probes having three...
Performance characteristics were experimentally determined for several sizes of a shielded and unshi...
A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling c...
To acquire heat transfer measurements of a high temperature Mach two flow a water-cooled calorimeter...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in ...
The design and construction of an altitude chamber, in which both pressure and temperature can be va...
An experimental temperature probe package containing a fluidic oscillator temperature probe and a sh...
A total temperature probe based on the recovery temperature of a circular cylinder is described whic...
Measuring of the total temperatures of the flowing medium is one of the pivotal points in the develo...
Local heat-transfer rates on the surface of a heated flat plate at zero incidence to an air stream f...
A new total temperature measurement correction is developed for the single-shielded type of probe. T...
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspe...
This report shows how the actual performance of an airplane varies with air temperature when the pre...
The aerodynamic environment in the test section of a hypersonic shock tunnel is very hostile as the ...