Author: H. F. Waldron
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 90
Book Description
Viscous Hypersonic Flow Over Pointed Cones at Low Reynolds Numbers
Author: H. F. Waldron
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 90
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 90
Book Description
Viscous Hypersonic Flows Over Pointed Cones at Low Reynolds Numbers
Author: H. F. Waldron
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0
Book Description
An experimental and analytical study of viscous hypersonic flow over pointed cones with particular emphasis on the viscous-layer regime is presented. Shock tunnel measurements of heat transfer to 5, 10 and 20 degree half-angle cones and of pressure on the 20 degree cone are compared with the predictions of a viscous-inviscid interaction analysis (Probstein and Elliot) including transverse curvature, of a viscous-layer nonslender cone analysis (Cheng) and of an extension of the nonslender cone analysis incorporating effects of slenderness. The large rise in heat transfer predicted by the transverse curvature theory is not observed and close agreement is obtained with the nonslender cone viscous-layer predictions. An extension of the nonslender cone analysis is presented where the effects of cone slenderness are included by a perturbation analysis. The solution of the resulting equations reveals that the net effect of transverse curvature and of other effects associated with cone slenderness is small in the viscous-layer regime for not-too-slender cones. Good agreement of the 10 and the 20 degree cone experimental data is obtained with this extension of the nonslender solution. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0
Book Description
An experimental and analytical study of viscous hypersonic flow over pointed cones with particular emphasis on the viscous-layer regime is presented. Shock tunnel measurements of heat transfer to 5, 10 and 20 degree half-angle cones and of pressure on the 20 degree cone are compared with the predictions of a viscous-inviscid interaction analysis (Probstein and Elliot) including transverse curvature, of a viscous-layer nonslender cone analysis (Cheng) and of an extension of the nonslender cone analysis incorporating effects of slenderness. The large rise in heat transfer predicted by the transverse curvature theory is not observed and close agreement is obtained with the nonslender cone viscous-layer predictions. An extension of the nonslender cone analysis is presented where the effects of cone slenderness are included by a perturbation analysis. The solution of the resulting equations reveals that the net effect of transverse curvature and of other effects associated with cone slenderness is small in the viscous-layer regime for not-too-slender cones. Good agreement of the 10 and the 20 degree cone experimental data is obtained with this extension of the nonslender solution. (Author).
Hypersonic Viscous Drag on Cones in Rarefied Flow
Author: Marvin I. Kussoy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 20
Book Description
Viscous Effects of Blunt Cones at Low Reynolds Numbers and Hypersonic Speeds
Author: G. M. Gregorek
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0
Book Description
Pressure and heat transfer rates on spherically-blunted 10 and 25 deg half angle cones at zero angle-of-attack were measured in a continuous flow hypersonic wind tunnel. At a nominal Mach number of 10, and Reynolds number between 3500 and 9700, based on free stream conditions and nose diameter, measured surface pressures were as high as 25% above the values predicted by solutions from the method of characteristics. A Tangent-Blunt-Cone analysis was formulated by coupling a local similarity boundary layer theory with the inviscid blunt cone solutions; use of this theory improved predictions to boundary layer theory at the higher stream densities; however, at Re
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0
Book Description
Pressure and heat transfer rates on spherically-blunted 10 and 25 deg half angle cones at zero angle-of-attack were measured in a continuous flow hypersonic wind tunnel. At a nominal Mach number of 10, and Reynolds number between 3500 and 9700, based on free stream conditions and nose diameter, measured surface pressures were as high as 25% above the values predicted by solutions from the method of characteristics. A Tangent-Blunt-Cone analysis was formulated by coupling a local similarity boundary layer theory with the inviscid blunt cone solutions; use of this theory improved predictions to boundary layer theory at the higher stream densities; however, at Re
Measurements of the Drag of Slender Cones in Hypersonic Flow at Low Reynolds Numbers Using a Magnetic Suspension and Balance
Roll-damping Derivative Calculations for Spinning Sharp and Blunt Cones in Supersonic and Hypersonic Flow
Author: Arloe W. Mayne (Jr.)
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 28
Book Description
The boundary-layer equations in a Crocco variables form have been numerically solved for flow over spinning sharp and blunt cones at zero incidence to supersonic and hypersonic streams. Both laminar and turbulent flows have been treated, and for the blunt cases swallowing of the inviscid entropy layer by the boundary layer has been considered. The item of primary interest is roll damping, and results of a parametric study involving Mach number, Reynolds number, cone angle, and bluntness ratio are presented. Limited comparisons with experimental data and another method of computation are also presented. (Author).
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 28
Book Description
The boundary-layer equations in a Crocco variables form have been numerically solved for flow over spinning sharp and blunt cones at zero incidence to supersonic and hypersonic streams. Both laminar and turbulent flows have been treated, and for the blunt cases swallowing of the inviscid entropy layer by the boundary layer has been considered. The item of primary interest is roll damping, and results of a parametric study involving Mach number, Reynolds number, cone angle, and bluntness ratio are presented. Limited comparisons with experimental data and another method of computation are also presented. (Author).
Some Heat Transfer Problems in Hypersonic Flow
Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
Book Description
Scientific and Technical Aerospace Reports
Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow
Author: Max Kinslow
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 78
Book Description
The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 78
Book Description
The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
Effects of Angle of Attack and Bluntness on the Hypersonic Flow Over a 15 ̊semiapex Cone in Helium
Author: Joseph W. Cleary
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
Book Description