Heat Transfer and Boundary Layer in Conical Nozzles PDF Download
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Author: Donald R. Boldman Publisher: ISBN: Category : Heat Languages : en Pages : 68
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: Donald R. Boldman Publisher: ISBN: Category : Heat Languages : en Pages : 68
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: James F. Schmidt Publisher: ISBN: Category : Fluid mechanics Languages : en Pages : 68
Book Description
In order to provide a relatively simple heat-transfer prediction along a nozzle, a differential (similar-solution) analysis for the turbulent boundary layer is developed. This analysis along with a new correlation for the turbulent Prandtl number gives good agreement of the predicted with the measured heat transfer in the throat and supersonic regiono f the nozzle. Also, the boundary-layer variables (heat transfer, etc. ) can be calculated at any arbitrary location in the throat or supersonic region of the nozzle in less than a half minute of computing time (Lewis DCS 7094-7044).
Author: Donald R. Boldman Publisher: ISBN: Category : Heat Languages : en Pages : 36
Book Description
An empirical modification of an existing integral energy turbulent boundary layer method is proposed in order to improve the estimates of local heat transfer in converging-diverging nozzles and consequently, provide better assessments of the total or integrated heat transfer. The method involves the use of a modified momentum-heat analogy which includes an acceleration term comprising the nozzle geometry and free stream velocity. The original and modified theories are applied to heat transfer data from previous studies which used heated air in 30 deg - 15 deg, 45 deg - 15 deg, and 60 deg - 15 deg water-cooled nozzles.
Author: David E. Boylan Publisher: ISBN: Category : Aerodynamic heating Languages : en Pages : 68
Book Description
The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Author: Donald R. Boldman
Author: Donald R. Boldman
Author: Donald R. Boldman
Author: Donald R. Boldmann
Author: James F. Schmidt
Author: Donald R. Boldman
Author: Donald R. Boldman
Author: Donald R. Boldman
Author: Donald R. Boldman
Author: Robert W. Graham
Author: David E. Boylan