Design and Checkout of a High Speed Research Nozzle Evaluation Rig 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 Design and Checkout of a High Speed Research Nozzle Evaluation Rig PDF full book. Access full book title Design and Checkout of a High Speed Research Nozzle Evaluation Rig by Raymond S. Castner. Download full books in PDF and EPUB format.
Author: Raymond S. Castner
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Get Book Here
Book Description
Author: Raymond S. Castner
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 658
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 920
Get Book Here
Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792073816
Category :
Languages : en
Pages : 30
Get Book Here
Book Description
The High Flow Jet Exit Rig (HFJER) was designed to provide simulated mixed flow turbojet engine exhaust for one- seventh scale models of advanced High Speed Research test nozzles. The new rig was designed to be used at NASA Lewis Research Center in the Nozzle Acoustic Test Rig and the 8x6 Supersonic Wind Tunnel. Capabilities were also designed to collect nozzle thrust measurement, aerodynamic measurements, and acoustic measurements when installed at the Nozzle Acoustic Test Rig. Simulated engine exhaust can be supplied from a high pressure air source at 33 pounds of air per second at 530 degrees Rankine and nozzle pressure ratios of 4.0. In addition, a combustion unit was designed from a J-58 aircraft engine burner to provide 20 pounds of air per second at 2000 degrees Rankine, also at nozzle pressure ratios of 4.0. These airflow capacities were designed to test High Speed Research nozzles with exhaust areas from eighteen square inches to twenty-two square inches. Nozzle inlet flow measurement is available through pressure and temperature sensors installed in the rig. Research instrumentation on High Speed Research nozzles is available with a maximum of 200 individual pressure and 100 individual temperature measurements. Checkout testing was performed in May 1997 with a 22 square inch ASME long radius flow nozzle. Checkout test results will be summarized and compared to the stated design goals. Castner, Raymond S. and Wolter, John D. Glenn Research Center NASA-TM-113179, NAS 1.15:113179, AIAA Paper 98-0711, E-10943 RTOP 537-05-21-00...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 638
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1076
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 440
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 912
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Power resources
Languages : en
Pages : 1254
Get Book Here
Book Description
