An innovative inlet total-pressure distortion measurement rake has been designed and developed for the F/A-18 A/B/C/D aircraft inlet. The design was conceived by NASA and General Electric Aircraft Engines (Evendale, Ohio). This rake has been flight qualified and flown in the F-18 High Alpha Research Vehicle (HARV) at NASA Dryden Flight Research Center. The rake's eight-legged, one-piece wagon wheel design was developed at a reduced cost and offers reduced installation time compared with traditional designs. The rake features 40 dual measurement ports for both low- and high-frequency pressure measurements with the high-frequency transducer mounted at the port. The high-frequency transducer offers direct absolute pressure measurements from lo...
An experimental measurement system was developed and implemented by the NASA Glenn Research Center i...
A subsonic study of high-angle-of-attack gritting strategies was undertaken with a 0.06-scale model ...
Turbofan engine used for evaluating air jets as steady state inlet flow distortion devic
An innovative inlet total pressure distortion measurement rake has been designed and developed for t...
The effects of high-angle-of-attack flight on aircraft inlet aerodynamic characteristics were invest...
The performance and distortion levels of the right inlet of the F/A-18A High Alpha Research Vehicle ...
The F404-GE-400-powered F/A-18A High Alpha Research Vehicle (HARV) was used to examine the quality o...
The Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center is a unique test platfo...
The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion ...
A compressor face rake with an internal valve arrangement to permit nulling was designed, constructe...
Rake mounting design reduces aerodynamic-surface discontinuities to a minimum when installed in boun...
The F-18 High Alpha Research Vehicle has proven to be a useful research tool with many unique capabi...
Future aircraft turbine engines, both commercial and military, will have to be able to successfully ...
A 15 percent scale lightweight fighter type inlet forebody was tested in the Ames 14 foot transonic ...
An investigation was conducted to evaluate and improve the quality of the airflow to be supplied to ...
An experimental measurement system was developed and implemented by the NASA Glenn Research Center i...
A subsonic study of high-angle-of-attack gritting strategies was undertaken with a 0.06-scale model ...
Turbofan engine used for evaluating air jets as steady state inlet flow distortion devic
An innovative inlet total pressure distortion measurement rake has been designed and developed for t...
The effects of high-angle-of-attack flight on aircraft inlet aerodynamic characteristics were invest...
The performance and distortion levels of the right inlet of the F/A-18A High Alpha Research Vehicle ...
The F404-GE-400-powered F/A-18A High Alpha Research Vehicle (HARV) was used to examine the quality o...
The Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center is a unique test platfo...
The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion ...
A compressor face rake with an internal valve arrangement to permit nulling was designed, constructe...
Rake mounting design reduces aerodynamic-surface discontinuities to a minimum when installed in boun...
The F-18 High Alpha Research Vehicle has proven to be a useful research tool with many unique capabi...
Future aircraft turbine engines, both commercial and military, will have to be able to successfully ...
A 15 percent scale lightweight fighter type inlet forebody was tested in the Ames 14 foot transonic ...
An investigation was conducted to evaluate and improve the quality of the airflow to be supplied to ...
An experimental measurement system was developed and implemented by the NASA Glenn Research Center i...
A subsonic study of high-angle-of-attack gritting strategies was undertaken with a 0.06-scale model ...
Turbofan engine used for evaluating air jets as steady state inlet flow distortion devic