Add to ORKGA Williams International FJ44-3A 3000-lb thrust class turbofan engine was tested in the NASA Glenn Research Center s Aero-Acoustic Propulsion Laboratory. This report presents the test set-up and documents the test conditions. Farfield directivity, in-duct unsteady pressures, duct mode data, and phased-array data were taken and are reported separately
This report reviews all engine noise research conducted at the NASA Glenn Research Center over the p...
In an effort to identify test facilities that offer sonic boom measurement capabilities, an explorat...
The NASA Glenn Research Center's Advanced Noise Control Fan (ANCF) was developed in the early 1990s ...
The 9- by 15-Foot Low Speed Wind Tunnel has been used for acoustic testing for more than 40 years. T...
In February 2017, aerodynamic and acoustic testing was completed on a scale-model high bypass ratio ...
A comprehensive aeroacoustic research program called the Source Diagnostic Test was recently conclud...
The NASA Glenn Research Centers DGEN Aeropropulsion Research Turbofan (DART) is based on the Price I...
NASA and GE teamed to design and build a 57 percent engine scaled fan stage for a Mach 4 variable cy...
The NASA Glenn Research Center's DGEN Aero-propulsion Research Turbofan (DART) is based on the Price...
An Ultrasonic Configurable Fan Artificial Noise Source (UCFANS) was designed, built, and tested in s...
NASA is interested in developing technology that leads to more routine, safe, and affordable access ...
This report summarizes results of the Hybrid Wing Body (HWB) N2A-EXTE model aeroacoustic test. The N...
The design of effective new technologies to reduce aircraft propulsion noise is dependent on identif...
This final report has been prepared by Honeywell Aerospace, Phoenix, Arizona, a unit of Honeywell In...
This report discusses work that began in mid-2004 sponsored by the Office of the Secretary of Defens...
This report reviews all engine noise research conducted at the NASA Glenn Research Center over the p...
In an effort to identify test facilities that offer sonic boom measurement capabilities, an explorat...
The NASA Glenn Research Center's Advanced Noise Control Fan (ANCF) was developed in the early 1990s ...
The 9- by 15-Foot Low Speed Wind Tunnel has been used for acoustic testing for more than 40 years. T...
In February 2017, aerodynamic and acoustic testing was completed on a scale-model high bypass ratio ...
A comprehensive aeroacoustic research program called the Source Diagnostic Test was recently conclud...
The NASA Glenn Research Centers DGEN Aeropropulsion Research Turbofan (DART) is based on the Price I...
NASA and GE teamed to design and build a 57 percent engine scaled fan stage for a Mach 4 variable cy...
The NASA Glenn Research Center's DGEN Aero-propulsion Research Turbofan (DART) is based on the Price...
An Ultrasonic Configurable Fan Artificial Noise Source (UCFANS) was designed, built, and tested in s...
NASA is interested in developing technology that leads to more routine, safe, and affordable access ...
This report summarizes results of the Hybrid Wing Body (HWB) N2A-EXTE model aeroacoustic test. The N...
The design of effective new technologies to reduce aircraft propulsion noise is dependent on identif...
This final report has been prepared by Honeywell Aerospace, Phoenix, Arizona, a unit of Honeywell In...
This report discusses work that began in mid-2004 sponsored by the Office of the Secretary of Defens...
This report reviews all engine noise research conducted at the NASA Glenn Research Center over the p...
In an effort to identify test facilities that offer sonic boom measurement capabilities, an explorat...
The NASA Glenn Research Center's Advanced Noise Control Fan (ANCF) was developed in the early 1990s ...