An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. Performance of the original and modified engines is compared for a range of simulated flight conditions. The performance data are generalized to show the applicability of methods used to estimate perfo...
The overall engine performance and the starting and windmilling characteristics of an XT38-A-2 turbo...
The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag ch...
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow tur...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
The overall engine performance and the starting and windmilling characteristics of an XT38-A-2 turbo...
The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag ch...
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow tur...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performanc...
The overall engine performance and the starting and windmilling characteristics of an XT38-A-2 turbo...
The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag ch...
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow tur...