The performance of the 11-stage axial-flow compressor in the X24C-4B turbojet engine was analyzed on the basis of results obtained from an investigation of the complete engine in the NACA Cleveland altitude wind tunnel. The engine was operated with four, exhaust nozzles of different outlet area over a range of engine speeds from 6000 to 12,500 rpm, corrected engine speeds from approximately 6100 to 13,600 rpm, and compressor Mach numbers from 0.45 to 1.00. Data are presented for engine operation over a range of simulated altitudes from 15,000 to 45,000 feet and simulated flight Mach numbers from 0.24 to 1.08
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Com...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet vel...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and...
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...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
An investigation has been conducted by the NACA to determine the design-performance characteristics ...
An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational ch...
"As part of an investigation of the performance and operational characteristics of the axial-flow ga...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NA...
Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 ...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Com...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet vel...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and...
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...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
An investigation has been conducted by the NACA to determine the design-performance characteristics ...
An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational ch...
"As part of an investigation of the performance and operational characteristics of the axial-flow ga...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NA...
Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 ...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Com...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...