Add to ORKGThe design of an aircraft engine capable of developing 186 kW shaft power at a 7620 m altitude is described. The 186 kW design takes into account expected new developments in aircraft designs resulting in a reassessment of the power requirements at the cruise mode operation. Based on the results of this analysis a three phase technology development program is projected resulting in production dates of 1985, 1992, and 2000
The results of a thermodynamic cycle (SFC) and weight analysis performed to establish engine configu...
Parametric design and mission evaluations of advanced turbofan configurations were conducted for fut...
The three engine programs that constitute the propulsion portion of NASA's Aircraft Energy Efficienc...
An experimental Single Cylinder Test Engine Program is conducted to confirm the analytically project...
A technology base of new developments which offered potential benefits to a general aviation engine ...
The status of NASA's Energy Efficient Engine Project, a comparative government-industry effort aimed...
Design studies of advanced multifuel general aviation and commuter aircraft rotary stratified charge...
Definitions of takeoff gross weight, performance, and direct operating cost for both a 30 and 50 pas...
Two different engines were studied. The advantages of a diesel to general aviation were reduced to f...
Performance, weight, size, and maintenance data for advanced rotary aircraft engines suitable for co...
The purpose of this paper is to give an outline of the present state of development and point out th...
The Energy Efficient Engine Project is directed at providing, by 1984, the advanced technologies whi...
High power density, low weight, compact dimensions, high efficiency as well as reliability are the k...
The near-term technology improvements which can reduce the fuel consumed in the JT9D, JT8D, and JT3D...
High power density, low weight, compact dimensions, high efficiency as well as reliability are the k...
The results of a thermodynamic cycle (SFC) and weight analysis performed to establish engine configu...
Parametric design and mission evaluations of advanced turbofan configurations were conducted for fut...
The three engine programs that constitute the propulsion portion of NASA's Aircraft Energy Efficienc...
An experimental Single Cylinder Test Engine Program is conducted to confirm the analytically project...
A technology base of new developments which offered potential benefits to a general aviation engine ...
The status of NASA's Energy Efficient Engine Project, a comparative government-industry effort aimed...
Design studies of advanced multifuel general aviation and commuter aircraft rotary stratified charge...
Definitions of takeoff gross weight, performance, and direct operating cost for both a 30 and 50 pas...
Two different engines were studied. The advantages of a diesel to general aviation were reduced to f...
Performance, weight, size, and maintenance data for advanced rotary aircraft engines suitable for co...
The purpose of this paper is to give an outline of the present state of development and point out th...
The Energy Efficient Engine Project is directed at providing, by 1984, the advanced technologies whi...
High power density, low weight, compact dimensions, high efficiency as well as reliability are the k...
The near-term technology improvements which can reduce the fuel consumed in the JT9D, JT8D, and JT3D...
High power density, low weight, compact dimensions, high efficiency as well as reliability are the k...
The results of a thermodynamic cycle (SFC) and weight analysis performed to establish engine configu...
Parametric design and mission evaluations of advanced turbofan configurations were conducted for fut...
The three engine programs that constitute the propulsion portion of NASA's Aircraft Energy Efficienc...