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 Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download 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 full book. Access full book title 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 by United States. National Aeronautics and Space Administration. Download full books in PDF and EPUB format.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722239374
Category :
Languages : en
Pages : 32
Get Book Here
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...
Author: Jon K. Holzman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Get Book Here
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Get Book Here
Book Description
Author: Albert C. Piccirillo
Publisher:
ISBN: 9781626830226
Category : Airplanes, Military
Languages : en
Pages : 328
Get Book Here
Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792725906
Category : Science
Languages : en
Pages : 34
Get Book Here
Book Description
The exhaust jet conditions, in terms of temperature and Mach number, were determined for a nozzle-aft end acoustic study flown on an F-15 aircraft. Jet properties for the F100 EMD engines were calculated using the engine manufacturer's specification deck. The effects of atmospheric temperature on jet Mach number, M10, were calculated. Values of turbine discharge pressure, PT6M, jet Mach number, and jet temperature were calculated as a function of aircraft Mach number, altitude, and power lever angle for the test day conditions. At a typical test point with a Mach number of 0.9, intermediate power setting, and an altitude of 20,000 ft, M10 was equal to 1.63. Flight measured and calculated values of PT6M were compared for intermediate power at altitudes of 15500, 20500, and 31000 ft. It was found that at 31000 ft, there was excellent agreement between both, but for lower altitudes the specification deck overpredicted the flight data. The calculated jet Mach numbers were believed to be accurate to within 2 percent. Hernandez, Francisco J. and Burcham, Frank W., Jr. Armstrong Flight Research Center NASA-TM-100419, H-1449, NAS 1.15:100419 RTOP 533-02-02...
Author: David C. Aronstein
Publisher: AIAA
ISBN: 9781600867903
Category : F-22 (Jet fighter plane)
Languages : en
Pages : 332
Get Book Here
Book Description
Author: Joseph R. Chambers
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 406
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721983452
Category :
Languages : en
Pages : 492
Get Book Here
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...
Author: David C. Aronstein
Publisher: AIAA
ISBN: 9781563471933
Category : Airplanes, Military
Languages : en
Pages : 78
Get Book Here
Book Description
This case study outlines the development of the Lightweight Fighter program, including the development, technology, and flight test history of the YF-16 and YF-17. The streamlined and highly successful Lightweight Fighter program effectively used experimental prototypes to introduce a set of new and advanced technologies to fighter aircraft, and serves as an excellent example of technology management, risk reduction in the development process, and acquisition philosophy.
