Add to ORKGA study was conducted to assess the performance potential of a supersonic through-flow fan engine for supersonic cruise aircraft. It included a mean-line analysis of fans designed to operate with in-flow velocities ranging from subsonic to high supersonic speeds. The fan performance generated was used to estimate the performance of supersonic fan engines designed for four applications: a Mach 2.3 supersonic transport, a Mach 2.5 fighter, a Mach 3.5 cruise missile, and a Mach 5.0 cruise vehicle. For each application an engine was conceptualized, fan performance and engine performance calculated, weight estimates made, engine installed in a hypothetical vehicle, and mission analysis was conducted
A computational analysis of a Gulfstream isentropic external compression supersonic inlet coupled to...
A study program for conceptual design studies of remote lift and lift/cruise fan systems to meet the...
An isolated 1.15 pressure ratio turbofan engine simulator was tested at Mach numbers from 0.6 to 0.8...
Engine performance and mission studies were carried out for turbofan engines equipped with supersoni...
Increased need for more efficient long-range supersonic flight has revived interest in the supersoni...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
Engine airframe integration effects are investigated for supersonic through-flow fan engines install...
Supersonic throughflow fan research, and technology needs are reviewed. The design of a supersonic t...
A study was made to evaluate potential improvement to a commercial supersonic transport by powering ...
Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the superson...
From Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic through-flow...
NASA and GE teamed to design and build a 57 percent engine scaled fan stage for a Mach 4 variable cy...
The concept of a variable cycle turbofan engine with an axially supersonic fan stage as powerplant f...
The NASA Lewis Research Center has embarked on a program to experimentally prove the concept of a su...
A conceptual design analysis is performed on a single engine V/STOL supersonic fighter/attack concep...
A computational analysis of a Gulfstream isentropic external compression supersonic inlet coupled to...
A study program for conceptual design studies of remote lift and lift/cruise fan systems to meet the...
An isolated 1.15 pressure ratio turbofan engine simulator was tested at Mach numbers from 0.6 to 0.8...
Engine performance and mission studies were carried out for turbofan engines equipped with supersoni...
Increased need for more efficient long-range supersonic flight has revived interest in the supersoni...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
Engine airframe integration effects are investigated for supersonic through-flow fan engines install...
Supersonic throughflow fan research, and technology needs are reviewed. The design of a supersonic t...
A study was made to evaluate potential improvement to a commercial supersonic transport by powering ...
Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the superson...
From Mach 3.20 cruise propulsion systems, preliminary design studies for two supersonic through-flow...
NASA and GE teamed to design and build a 57 percent engine scaled fan stage for a Mach 4 variable cy...
The concept of a variable cycle turbofan engine with an axially supersonic fan stage as powerplant f...
The NASA Lewis Research Center has embarked on a program to experimentally prove the concept of a su...
A conceptual design analysis is performed on a single engine V/STOL supersonic fighter/attack concep...
A computational analysis of a Gulfstream isentropic external compression supersonic inlet coupled to...
A study program for conceptual design studies of remote lift and lift/cruise fan systems to meet the...
An isolated 1.15 pressure ratio turbofan engine simulator was tested at Mach numbers from 0.6 to 0.8...