Add to ORKGPerformance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form
The altitude operational characteristics of the prototype J40-WE-8 turbojet engine were determined i...
Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from a...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation was conducted in the NACA Lewis altitude wind tunnel to evaluate the performance ch...
Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 ...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
An investigation has been conducted in the NACA Lewis altitude wind tunnel to evaluate the performan...
As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, ...
The performance of the 11-stage axial-flow compressor in the X24C-4B turbojet engine was analyzed on...
Pressures and temperatures throughout the X24C-4B turbojet engine are presented in both tabular and ...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
The overall engine performance and the starting and windmilling characteristics of an XT38-A-2 turbo...
An investigation was conducted in the NACA Lewis altitude wind tunnel to evaluate the performance ch...
The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes betw...
The altitude operational characteristics of the prototype J40-WE-8 turbojet engine were determined i...
Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from a...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation was conducted in the NACA Lewis altitude wind tunnel to evaluate the performance ch...
Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 ...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
An investigation has been conducted in the NACA Lewis altitude wind tunnel to evaluate the performan...
As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, ...
The performance of the 11-stage axial-flow compressor in the X24C-4B turbojet engine was analyzed on...
Pressures and temperatures throughout the X24C-4B turbojet engine are presented in both tabular and ...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
The overall engine performance and the starting and windmilling characteristics of an XT38-A-2 turbo...
An investigation was conducted in the NACA Lewis altitude wind tunnel to evaluate the performance ch...
The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes betw...
The altitude operational characteristics of the prototype J40-WE-8 turbojet engine were determined i...
Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from a...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...