Flight and Static Exhaust Flow Properties of an F110-Ge-129 Engine in an F-16xl Airplane During Acoustic Tests

Flight and Static Exhaust Flow Properties of an F110-Ge-129 Engine in an F-16xl Airplane During Acoustic Tests PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722239374
Category :
Languages : en
Pages : 32

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Book Description
The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LARC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented. Holzman, Jon K. and Webb, Lannie D. and Burcham, Frank W., Jr. Armstrong Flight Research Center RTOP 505-68-10...

Flight and Static Exhaust Flow Properties of an F110-Ge-129 Engine in an F-16xl Airplane During Acoustic Tests

Flight and Static Exhaust Flow Properties of an F110-Ge-129 Engine in an F-16xl Airplane During Acoustic Tests PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722239374
Category :
Languages : en
Pages : 32

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Book Description
The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LARC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented. Holzman, Jon K. and Webb, Lannie D. and Burcham, Frank W., Jr. Armstrong Flight Research Center RTOP 505-68-10...

Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests

Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests

Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests PDF Author: Jon K. Holzman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26

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Book Description
The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LaRC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented.

FLIGHT AND STATIC EXHAUST FLOW PROPERTIES OF AN F110-GE-129 ENGINE IN AN F-16XL AIRPLANE DURING ACOUSTIC TESTS... NASA-TM-104326... MAR. 31

FLIGHT AND STATIC EXHAUST FLOW PROPERTIES OF AN F110-GE-129 ENGINE IN AN F-16XL AIRPLANE DURING ACOUSTIC TESTS... NASA-TM-104326... MAR. 31 PDF Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :

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F-16XL and F-18 High Speed Acoustic Flight Test Databases

F-16XL and F-18 High Speed Acoustic Flight Test Databases PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 276

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Software Engineering and Formal Methods. SEFM 2021 Collocated Workshops

Software Engineering and Formal Methods. SEFM 2021 Collocated Workshops PDF Author: Antonio Cerone
Publisher: Springer Nature
ISBN: 3031124294
Category : Computers
Languages : en
Pages : 355

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Book Description
This volume constitutes revised selected papers from the four workshops collocated with the 19th International Conference on Software Engineering and Formal Methods, SEFM 2021, held virtually during December 6–10, 2021. The 21 contributed papers presented in this volume were carefully reviewed and selected from a total of 29 submissions. The book also contains 3 invited talks. SEFM 2021 presents the following four workshops: CIFMA 2021 - 3rd International Workshop on Cognition: Interdisciplinary Foundations, Models and Applications;CoSim-CPS 2021 - 5th Workshop on Formal Co-Simulation of Cyber-Physical Systems;OpenCERT 2021 - 10th International Workshop on Open Community approaches to Education, Research and Technology;ASYDE 2021 - 3rd International Workshop on Automated and verifiable Software sYstem Development. Due to the Corona pandemic this event was held virtually.

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 900

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Ground and In-flight Acoustic and Performance Characteristics of Jet-aircraft Exhaust Noise Supressors

Ground and In-flight Acoustic and Performance Characteristics of Jet-aircraft Exhaust Noise Supressors PDF Author: Willard D. Coles
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 54

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Engine Exhaust Characteristics Evaluation in Support of Aircraft Acoustic Testing

Engine Exhaust Characteristics Evaluation in Support of Aircraft Acoustic Testing PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16

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Results of Aero/Acoustic Tests and Analytical Studies of a Two-Dimensional Eight-Lobe Mixer-Ejector Exhaust Nozzle at Takeoff Conditions

Results of Aero/Acoustic Tests and Analytical Studies of a Two-Dimensional Eight-Lobe Mixer-Ejector Exhaust Nozzle at Takeoff Conditions PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721983452
Category :
Languages : en
Pages : 492

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Book Description
Hot flow aero-acoustic tests were conducted with Pratt & Whitney's High-Speed Civil Transport (HSCT) Mixer-Ejector Exhaust Nozzles by General Electric Aircraft Engines (GEAE) in the GEAE Anechoic Freejet Noise Facility (Cell 41) located in Evendale, Ohio. The tests evaluated the impact of various geometric and design parameters on the noise generated by a two-dimensional (2-D) shrouded, 8-lobed, mixer-ejector exhaust nozzle. The shrouded mixer-ejector provides noise suppression by mixing relatively low energy ambient air with the hot, high-speed primary exhaust jet. Additional attenuation was obtained by lining the shroud internal walls with acoustic panels, which absorb acoustic energy generated during the mixing process. Two mixer designs were investigated, the high mixing "vortical" and aligned flow "axial", along with variations in the shroud internal mixing area ratios and shroud length. The shrouds were tested as hardwall or lined with acoustic panels packed with a bulk absorber. A total of 21 model configurations at 1:11.47 scale were tested. The models were tested over a range of primary nozzle pressure ratios and primary exhaust temperatures representative of typical HSCT aero thermodynamic cycles. Static as well as flight simulated data were acquired during testing. A round convergent unshrouded nozzle was tested to provide an acoustic baseline for comparison to the test configurations. Comparisons were made to previous test results obtained with this hardware at NASA Glenn's 9- by 15-foot low-speed wind tunnel (LSWT). Laser velocimetry was used to investigate external as well as ejector internal velocity profiles for comparison to computational predictions. Ejector interior wall static pressure data were also obtained. A significant reduction in exhaust system noise was demonstrated with the 2-D shrouded nozzle designs. Harrington, Douglas (Technical Monitor) and Schweiger, P. and Stern, A. and Gamble, E. and Barber, T. and Chiappe...