Add to ORKGWind tunnel tests of subsonic aerodynamic characteristics of large scale tip turbine cruise fan with 1.075 pressure ratio at angle of attac
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
The low-speed aerodynamic characteristics of large scale V/STOL transport models with lift fan and l...
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subs...
Aerodynamic and acoustic measurements at a typical STOL aircraft takeoff and landing velocity demons...
Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach number
Aerodynamic characteristics of lift fan installation for direct lift V/STOL aircraf
An experimental, aerodynamic investigation was made of two 1.83 m diameter fan systems which are bei...
A low speed wind tunnel test of a fixed lip inlet with engine, was performed. The inlet was close co...
An inlet model designed for high angle of attack capability, coupled to a .508 m tip diameter turbof...
At a typical STOL aircraft takeoff and landing velocity, wind tunnel aerodynamic and acoustic measur...
Partial admission performance was obtained for a 0.4 linear scale version of the LF460 lift fan turb...
An isolated 1.15 pressure ratio turbofan engine simulator was tested at Mach numbers from 0.6 to 0.8...
An investigation was conducted in the NASA-Ames 40 by 80 Foot Wind Tunnel to determine the aerodynam...
Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach numbers.Includes ...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
The low-speed aerodynamic characteristics of large scale V/STOL transport models with lift fan and l...
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subs...
Aerodynamic and acoustic measurements at a typical STOL aircraft takeoff and landing velocity demons...
Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach number
Aerodynamic characteristics of lift fan installation for direct lift V/STOL aircraf
An experimental, aerodynamic investigation was made of two 1.83 m diameter fan systems which are bei...
A low speed wind tunnel test of a fixed lip inlet with engine, was performed. The inlet was close co...
An inlet model designed for high angle of attack capability, coupled to a .508 m tip diameter turbof...
At a typical STOL aircraft takeoff and landing velocity, wind tunnel aerodynamic and acoustic measur...
Partial admission performance was obtained for a 0.4 linear scale version of the LF460 lift fan turb...
An isolated 1.15 pressure ratio turbofan engine simulator was tested at Mach numbers from 0.6 to 0.8...
An investigation was conducted in the NASA-Ames 40 by 80 Foot Wind Tunnel to determine the aerodynam...
Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach numbers.Includes ...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
The low-speed aerodynamic characteristics of large scale V/STOL transport models with lift fan and l...