Wall Heat Transfer Effects on Supersonic Nozzle Wall Boundary-layer Temperature Profiles 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 Wall Heat Transfer Effects on Supersonic Nozzle Wall Boundary-layer Temperature Profiles PDF full book. Access full book title Wall Heat Transfer Effects on Supersonic Nozzle Wall Boundary-layer Temperature Profiles by Walter B. Sturek. Download full books in PDF and EPUB format.
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Get Book Here
Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Get Book Here
Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
Get Book Here
Book Description
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
Get Book Here
Book Description
A review of a comprehensive experimental investigation of the heat transfer and boundary layer in 30 deg to 15 deg and 60 deg to 15 deg conical nozzles is presented. The experiments were conducted with air at a stagnation temperature of 539 K (970 R) and throat Reynolds numbers based on a diameter ranging from 6 x 10 to the 5th power to 5 x 10 to the 6th power. Nozzle wall surface finish was varied from a smooth machine finish to a 826 x 10 to the minus 6th power cm (325 x 10 to the minus 6th in.) rms sandblasted finish. Measured heat transfer and wall temperatures are tabulated.
Author: David F. Gates
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
Get Book Here
Book Description
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 558
Get Book Here
Book Description
Author: D. K. Walsh
Publisher:
ISBN:
Category :
Languages : en
Pages : 358
Get Book Here
Book Description
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 92
Get Book Here
Book Description
Author: Roland E. Lee
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 114
Get Book Here
Book Description
The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
Get Book Here
Book Description
