Author: Publisher:
ISBN:
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Languages : en
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Book Description
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Author: Near Wake Flow Studies in Supersonic Flow
Author: Josef RomAnalysis of the Near Wake Pressure in Supersonic Flow Using the Momentum Integral Method
Author: Josef RomPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
Book Description
The pressure of two-dimensional base type separated regions is evaluated by use of semi-empirical analysis. The analysis is based on the momentum integral method. Empirical parameters required in the analysis are evaluated from various available experimental data. Good correlation over a large range of variation of the physical parameters is obtained in the cases of two-dimensional supersonic flows for both laminar and turbulent separation over backward facing steps and blunt bases. The axially symmetric base type flows seem to be affected by the inviscid axially symmetric external flow in a different manner than found in the two dimensional case. It seems that the parameters applicable for the two-dimensional base type flows are not sufficient for the correlation of the axially symmetric separated flows. (Author).
Laminar Supersonic Flow in Near Wakes at High Values of Reynolds Number
Author: M. Yousuff HussainiPublisher:
ISBN:
Category :
Languages : en
Pages : 112
Book Description
The studies of subsonic and supersonic wake flows are reviewed. A systematic technique of obtaining non-similar solutions to the boundary layer equations governing the laminar compressible mixing behind a finite base is developed and applied to the case of supersonic base flow. Chapman's similarity solution emerges as the first term in the asymptotic expansion. The analysis takes into account the finiteness of the base, eliminates the infinite velocity of slip at the base present in Chapman's solution, and predicts reverse flow in the 'dead-air' region. (Author).
Experimental and Theorectical Investigation of the Near Wake in an Axisymmetric Supersonic Flow with and Without Base Injection
Author: Ram SinhaPublisher:
ISBN:
Category :
Languages : en
Pages : 70
Book Description
Results of an experimental and theoretical investigation of the near wake in an axisymmetric flow past a slender body at Mach number 3.92 with and without base injection are presented. For the experimental part centerline distributions of pressure, temperature, Mach number, velocity, and concentration were obtained. Turbulent as well as laminar flow fields were investigated for the zero injection case. Base injection problem was studied only in the turbulent flow case using gaseous hydrogen, helium, nitrogen, and argon as injectants. A special effort was made to study the variation of pressure, velocity, and Mach number at the base with base injection. For the theoretical part an expression was developed to calculate the centerline distribution of turbulent viscosity from experimental profiles using full Navier-Stokes equations; flow fields with non-zero pressure gradients were considered. Using this expression, centerline viscosity distributions for various cases of wake flow and coaxial mixing were calculated and the results compared with those obtained from the empirical models. (Author).
Analytical Nodel of Supersonic, Turbulent, Near-wake Flows
Author: C. E. PetersPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Book Description
An analytical model for planar and axisymmetric, supersonic, turbulent, near-wake flows is presented. The viscous region behind the blunt base is described by the integral form of the boundary-layer equations, and the inviscid outer-flow region, including the remnant of the initial turbulent boundary layer, is computed with the rotational method of characteristics. The solution of the two regions is fully coupled. The saddle-point singularity, similar to the Crocco-Lees critical point, occurs downstream of the rear stagnation point. The base pressure is obtained by iteration of the initial conditions until the flow-field solution will pass through the singularity. Base bleed of a gas different from the outer-stream gas is included in the formulation, and provision is made to treat equilibrium chemical reactions in the viscous wake. However, an unresolved problem has been encountered in the solution of the species conservation equations. Therefore, results for only single gas flows are presented. The analytical model is shown to adequately predict the effect of free-stream Mach number and initial boundary layer on the planar base pressure. In addition, the planar flow-field structure is well predicted. Axisymmetric base pressure and flow-field structure are reasonably well predicted for free-stream Mach numbers greater than 2.0, but the turbulent transport model used yields only fair results for Mach numbers less than 1.7. The effect of base bleed on the axisymmetric base pressure is well predicted. (Author).
Particle Image Velocimetry
Author: Andreas SchröderPublisher: Springer Science & Business Media
ISBN: 3540735283
Category : Science
Languages : en
Pages : 516
Book Description
This book summarizes the main results reached using the EC-funded network PivNet 2. It also presents a survey of the state of the art of scientific research using PIV techniques. You get a clear introduction to the basics of these techniques. The authors then guide you through current and possible future applications for flow analysis, including combustion and supersonic flow. Hundreds of illustrations, many in full color, are provided.
Analysis of Supersonic Far Wake Flow Past Two-dimensional and Axisymmetric Pointed Bodies Using the Method of Integral Relations
Author: Prabhakara Poovandur RaoPublisher:
ISBN:
Category :
Languages : en
Pages : 424
Book Description
Experimental and Theoretical Investigation of the Near Wake Behind a Rearward Facing Step in Supersonic Flow
Author: Howard Edwin SmithPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
Book Description
Author: Ramlala P. Sinha