Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 252
Book Description
Heat Transfer to a Full-coverage Film-cooled Surface with 30 Degrees Slant-hole Injection
Author: Heat Transfer to a Full-coverage Film-cooled Surface with 30 Degree Slant-hole Injection
Author: Heat Transfer to a Full-coverage, Film-cooled Surface with Compound-angle (30 Deg and 45 Deg) Hole Injection
Author: H. K. KimPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 164
Book Description
An experimental study of heat transfer was conducted on a turbulent boundary layer with full-coverage film cooling through an array of holes inclined at 30 degrees to the surface and 45 degrees to the flow direction.
Full Coverage Film Cooling Heat Transfer Studies: a Summary of the Data for Normal Hole Injection and 30 Degrees Slant Hole Injection
Author: Stanford University. Thermosciences Division. Thermosciences DivisionPublisher:
ISBN:
Category :
Languages : en
Pages : 110
Book Description
Full-coverage Film Cooling Heat Transfer Study: Summary of Data for Normal-hole Injection and 30 Deg Slant-hole Injection
Author: Heat Transfer to a Full Coverage Film Cooled Surface with Thirty Degree Slant Hole Injection
Author: Stanford University. Thermosciences Division. Thermosciences DivisionPublisher:
ISBN:
Category :
Languages : en
Pages : 264
Book Description
Full-coverage Film Cooling Heat Transfer Studies - a Summary of the Data for Normal-hole Injection and 30 Degree Stant-hole Injection
Author: M. E. CrawfordPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Results are presented from a study of heat transfer to a full-coverage, film-cooled turbulent boundary layer over a flat surface. The surface used in the investigation consists of a discrete hole test section, containing eleven.
Full-coverage Film Cooling Heat Transfer Study
Author: Heat transfer to a full-coverage film-cooled surface with 30 ̊slant-hole injection
Author: Michael E. CrawfordPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 256
Book Description
Heat transfer behavior was studied in a turbulent boundary layer with full coverage film cooling through an array of discrete holes and with injection 30 deg to the wall surface in the downstream direction. Stanton numbers were measured for a staggered hole pattern with pitch-to-diameter ratios of 5 and 10, an injection mass flux ratio range of 0.1 to 1.3, and a range of Reynolds number Re sub x of 150,000 to 5 million. Air was used as the working fluid, and the mainstream velocity varied from 9.8 to 34.2 m/sec (32 to 112 ft/sec). The data were taken for secondary injection temperature equal to the wall temperature and also equal to the mainstream temperature. The data may be used to obtain Stanton number as a continuous function of the injectant temperature by use of linear superposition theory. The heat transfer coefficient is defined on the basis of a mainstream-to-wall temperature difference. This definition permits direct comparison of performance between film cooling and transpiration cooling. A differential prediction method was developed to predict the film cooling data base. The method utilizes a two-dimensional boundary layer program with routines to model the injection process and turbulence augmentation. The program marches in the streamwise direction, and when a row of holes is encountered, it stops and injects fluid into the boundary layer. The turbulence level is modeled by algebraically augmenting the mixing length, with the augmentation keyed to a penetration distance for the injected fluid.--(NTRL site)
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 756
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.