Add to ORKGThe NASA Lewis Research Center has embarked on a program to experimentally prove the concept of a supersonic through-flow fan which is to maintain supersonic velocities throughout the compression system with only weak shock-wave flow losses. The detailed design of a supersonic through-flow fan and estimated off-design performance with the use of advanced computational codes are described. A multistage compressor facility is being modified for the newly designed supersonic through-flow fan and the major aspects of this modification are briefly described
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subs...
Inlet noise and aerodynamic performance are presented for a high tip speed fan designed with rotor b...
Three propulsion systems for a Mach 2 STOVL fighter were compared. The three propulsion systems are:...
Supersonic throughflow fan research, and technology needs are reviewed. The design of a supersonic t...
Increased need for more efficient long-range supersonic flight has revived interest in the supersoni...
Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the superson...
Engine performance and mission studies were carried out for turbofan engines equipped with supersoni...
A study was conducted to assess the performance potential of a supersonic through-flow fan engine fo...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
From Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic through-flow...
Engine airframe integration effects are investigated for supersonic through-flow fan engines install...
A conceptual design analysis is performed on a single engine V/STOL supersonic fighter/attack concep...
The aerodynamic performance of a representative supersonic cruise inlet was investigated using a fan...
Methods for designing supersonic stator and rotor blading corrected for boundary layer displacement ...
A study was made to evaluate potential improvement to a commercial supersonic transport by powering ...
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subs...
Inlet noise and aerodynamic performance are presented for a high tip speed fan designed with rotor b...
Three propulsion systems for a Mach 2 STOVL fighter were compared. The three propulsion systems are:...
Supersonic throughflow fan research, and technology needs are reviewed. The design of a supersonic t...
Increased need for more efficient long-range supersonic flight has revived interest in the supersoni...
Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the superson...
Engine performance and mission studies were carried out for turbofan engines equipped with supersoni...
A study was conducted to assess the performance potential of a supersonic through-flow fan engine fo...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
From Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic through-flow...
Engine airframe integration effects are investigated for supersonic through-flow fan engines install...
A conceptual design analysis is performed on a single engine V/STOL supersonic fighter/attack concep...
The aerodynamic performance of a representative supersonic cruise inlet was investigated using a fan...
Methods for designing supersonic stator and rotor blading corrected for boundary layer displacement ...
A study was made to evaluate potential improvement to a commercial supersonic transport by powering ...
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subs...
Inlet noise and aerodynamic performance are presented for a high tip speed fan designed with rotor b...
Three propulsion systems for a Mach 2 STOVL fighter were compared. The three propulsion systems are:...