Combustion 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 conducted. Performance...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
A brief investigation has been made of the performance of a single combustor of the TG-180 turboJet ...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
A preliminary investigation of the over-all performance of a simply constructed, short-life, turboje...
An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational ch...
An investigation was conducted in the combustor of a 3000-pound-thrust turbojet engine to determine ...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
Thrust augmentation of an axial-flow type turbojet engine by burning fuel in the tail pipe has been ...
A preliminary investigation of an axial-flow gas turbine-propeller engine was conducted. Performance...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
A brief investigation has been made of the performance of a single combustor of the TG-180 turboJet ...
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were det...
An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the opera...
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-...
Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine...
The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-ty...
A preliminary investigation of the over-all performance of a simply constructed, short-life, turboje...
An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational ch...
An investigation was conducted in the combustor of a 3000-pound-thrust turbojet engine to determine ...
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust ax...
An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the perfo...
Thrust augmentation of an axial-flow type turbojet engine by burning fuel in the tail pipe has been ...
A preliminary investigation of an axial-flow gas turbine-propeller engine was conducted. Performance...
Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was det...
A brief investigation has been made of the performance of a single combustor of the TG-180 turboJet ...