Performance Characterization of a Radiatively Driven Hypersonic Wind Tunnel 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 Performance Characterization of a Radiatively Driven Hypersonic Wind Tunnel PDF full book. Access full book title Performance Characterization of a Radiatively Driven Hypersonic Wind Tunnel by R. W. Anderson. Download full books in PDF and EPUB format.
Author: R. W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: R. W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 134
Get Book Here
Book Description
Results and analysis of the RDHWT/MARlAH II 1 MW experiment are reported. The experiment is the addition of approximately MW of energy to a supersonic air flow with an electron bean. The experiment hardware, arrangement and conduct are described. Selected data and analysis are reported. The experiment was subject to transient power fluctuations flat were traced to the electron beam source rather than to flow instability. Power stability was established at lower power conditions. and these data were used for selected code validations.
Author: George Luthringer
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 0
Get Book Here
Book Description
Predicted values of the important performance parameters for the Aeronautical Research Laboratory's new 30-inch (nozzle exit diameter) hypersonic wind tunnel are discussed. Included are curves giving tunnel Reynold's numbers per unit length, flight Reynold's number (with simulation capability indicated), degrees supersaturation, mass flow rates, normal shock recovery pressures, vacuum system characteristics, and running times. (Author).
Author: R. Miles
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Raheem Temitope Bello
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
In hypersonic wind tunnel testing, matching the flow enthalpy conditions for the hypersonic air-breathing corridor is of great importance in order to assure the validity of experimental results. The flow enthalpy of the UTA hypersonic shock tunnel is increased by a shock-induced detonation driver. The detonation mixture consist of hydrogen and oxygen in stoichiometric quantities (2H2+O2 --> 2H2O). Experimental variations of pressure and the volume of the detonation section were performed to characterize the enthalpy limits, and overall performance of the UTA hypersonic shock tunnel. The UTA HST test section was operated at a nominal Mach number of 10. Force balance experiments were performed in the test section during the high enthalpy characterization. Enthalpy measurements were also performed using a type K thermocouple placed in a Fay-Riddell probe within the test section. High enthalpy flows with maximum total temperature of 4393 K, maximum total pressure of 373 atm, and maximum total enthalpy of 5.1 MJ/kg were achieved in the driven section, with Mach numbers of 8.75 0.25 measured in the test section.
Author: Leon H. Schindel
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
Get Book Here
Book Description
This report documents the characterization and analysis of a high current power supply for the building 865 Hypersonic Wind Tunnel at Sandia National Laboratories. The system described in this report became operational in 2013, replacing the original 1968 system which employed an induction voltage regulator. This analysis and testing was completed to help the parent organization understand why an updated and redesigned power system was not delivering adequate power to resistive heater elements in the HWT. This analysis led to an improved understanding of the design and operation of the revised 2013 power supply system and identifies several reasons the revised system failed to achieve the performance of the original power supply installation. Design modifications to improve the performance of this system are discussed.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
Work conduced from August 1, 1992 until November 30,1996 under support from the Air Force Arnold Engineering Development Center (AEDC), followed by continuing support from the Air Force Research Laboratory through September 30,1998, established the foundation for the development of a new concept which is expected to extend the range of practical hypersonic wind tunnel testing from approximately Mach 8 to Mach 12 and beyond.
Author: Erik Hoberg
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
Author: Robert W. Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages : 360
Get Book Here
Book Description
