Author: J. A. Durand
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 1
Get Book Here
Book Description
A new method for the estimation of boundarylayer thickness corrections to the contours of cooled axisymmetric nozzles for low-density, hypersonic flows is presented. Laminar flows of real gases in thermodynamic equilibrium with possible variation of specific heats, frozen flows, and boundary-layer thicknesses of the order of nozzle radii are considered. The derivation combines an appropriate integral momentum relation with an approximate friction law based on local similarity. Results of application of the method to several typical cases are shown to agree closely with experimental data. (Author).
Author: Willard E. Summers
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 66
Get Book Here
Book Description
Author: Willard E. Summers
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Get Book Here
Book Description
Author: James J. White
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 394
Get Book Here
Book Description
Author: Arlo F. Johnson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 26
Get Book Here
Book Description
The excellent agreement between measured boundary layer thickness and thickness calculated by Sivells and Payne recommends their method for calculating turbulent boundary layer growth in axisymmetric hypersonic nozzles. It was thought worthwhile to adapt their approach to the laminar boundary layer. This analysis, along with a limited amount of corroborating data, is presented herein.
Author: David L. Whitfield
Publisher:
ISBN:
Category :
Languages : en
Pages : 92
Get Book Here
Book Description
The viscous flow region in low density hypersonic axisymmetric nozzles was investigated both theoretically and experimentally. Nonsimilar solutions were obtained for the internal laminar boundary layer equations which include second-order transverse curvature terms. These solutions were obtained on a CDC 1604 digital computer. Four existing low density axisymmetric nozzles were considered. Numerical solutions were obtained for these nozzles using various plenum chamber conditions and wall temperature distributions. The plenum chamber conditions used in the numerical solutions for these nozzles produced a test section Mach number range of about 3.0 to 18.0 and a test section Reynolds number per foot range of about 1000 to 15,000. Some results of the numerical solutions are compared with experimental measurements of pitot pressure, relative heat flux, and nozzle wall heat transfer coefficients. In all comparisons the numerical solutions appear to be consistent with the experimental data. (Author).
Author: E. S. Levinsky
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 54
Get Book Here
Book Description
Procedures are developed for determining the inviscid core and boundary layer development in diverging nozzles with high enthalpy reservoir conditions in which the gas composition has been displaced from equilibrium by chemical relaxation. A finite difference procedure, based on the method of characteristics, is used for the inviscid flow with finite rate chemical reactions. Laminar boundary layer profiles, based on local similarity, are obtained by integrating the coupled boundary layer and chemical reaction equations outward from the nozzle wall. Free stream boundary conditions on the chemical specie concentrations and the thermodynamic variables are satisfied by iterating o the unknow concentrations and derivatives at the wall. Numerical calculations are presented for the AEDC, VKF low density tunnel and the Convair hypersonic shock tunnel. Effects of chemical reactions in the boundary layer are restricted to the region in which the core flow has not yet frozen and in which the boundary layer is thin. When the boundary layer is thick enough to influence the core expansion, gas phase reactions are frozen. (Author).
Author: Mancil W. Milligan
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 56
Get Book Here
Book Description
Author: Virendrakumar Chaturbhai Patel
Publisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 46
Get Book Here
Book Description
An examination of the Reynolds equations for axisymmetric turbulent flow where the thickness of the boundary layer is of the same order as the transverse radius of curvature of the surface shows that neither the boundary layer nor the potential flow outside it may be calculated independently of the other, owing to significant interactions between the two flow regimes. Following a discussion of various procedures for extending conventional thin boundary-layer calculation methods to treat thick axisymmetric turbulent boundary-layers, a method is proposed for the simultaneous solution of the boundary layer and the potential flow equations, allowing the two flow regimes to interact. (Author Modified Abstract).
