Add to ORKGCombustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine
A preliminary investigation of an axial-flow gas turbine-propeller engine was conduxted. Performance...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow tur...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
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...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine...
An investigation to determine the performance and operational characteristics of an axial-flow gas t...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
A preliminary investigation of an axial-flow gas turbine-propeller engine was conduxted. Performance...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow tur...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
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...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine...
An investigation to determine the performance and operational characteristics of an axial-flow gas t...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
A preliminary investigation of an axial-flow gas turbine-propeller engine was conduxted. Performance...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...