Theoretical And Experimental Studies Of Ducted Mixing And Burning Of Coaxial Streams PDF Download
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Author | : C. E. Peters |
Publisher | : |
Total Pages | : 11 |
Release | : 1969 |
Genre | : Combustion |
ISBN | : |
Download Theoretical and Experimental Studies of Ducted Mixing and Burning of Coaxial Streams Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 772 |
Release | : 1994 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Author | : Turgut Sarpkaya |
Publisher | : |
Total Pages | : 392 |
Release | : 1970 |
Genre | : Fluid mechanics |
ISBN | : 9780804707442 |
Download Proceedings of the 1970 Heat Transfer and Fluid Mechanics Institute Book in PDF, ePub and Kindle
Author | : C. E. Peters |
Publisher | : |
Total Pages | : 72 |
Release | : 1978 |
Genre | : Jets |
ISBN | : |
Download Integral Analysis of Ducted Two-stream Mixing with Recirculation Book in PDF, ePub and Kindle
The integral boundary-layer equations are used to develop an analysis of ducted turbulent mixing of coaxial streams. Non-recirculating flows, as well as flows with a recirculation region along the duct wall, are considered in the formulation. The flow geometry considered is either axisymmetric or planar, and provision is made to calculate flows with a centerbody. Chemical reactions in the mixing process, if they occur, are assumed to be in equilibrium. A simple eddy viscosity model is used to describe the turbulent transport processes. Comparison of the analytical results with experiments indicates that the location and extent of recirculation are well predicted, at least for flows with moderate density gradients. However, because of the neglect of streamwise turbulent transport processes in the analysis, the predicted concentration field in recirculating flow is in only fair agreement with experiment. An extended integral analysis, in which the streamwise turbulent transport of momentum and species is included in an approximate manner, is formulated. (Author).
Author | : |
Publisher | : |
Total Pages | : 300 |
Release | : 1972 |
Genre | : Mechanics, Applied |
ISBN | : |
Download Applied Mechanics Reviews Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 288 |
Release | : 1970 |
Genre | : Aerodynamics |
ISBN | : |
Download A Collection of Technical Papers Book in PDF, ePub and Kindle
Author | : Kirti N. Ghia |
Publisher | : |
Total Pages | : 100 |
Release | : 1970 |
Genre | : Jets |
ISBN | : |
Download Turbulent Mixing in the Initial Region of Heterogeneous Axisymmetric Coaxial Confined Jets Book in PDF, ePub and Kindle
Author | : Philip Thomas Harsha |
Publisher | : |
Total Pages | : 340 |
Release | : 1971 |
Genre | : Turbulence |
ISBN | : |
Download Free Turbulent Mixing Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 448 |
Release | : 1975 |
Genre | : Mechanical engineering |
ISBN | : |
Download ASME Technical Papers Book in PDF, ePub and Kindle
Author | : C. E. Peters |
Publisher | : |
Total Pages | : 30 |
Release | : 1976 |
Genre | : Rocket engines |
ISBN | : |
Download An Approximate Analysis of the Shock Structure in Underexpanded Plumes Book in PDF, ePub and Kindle
An approximate analytical model has been developed for computing the first cycle of the shock structure in plumes from underexpanded axisymmetric supersonic nozzles. The physical basis of the model is the same as that of the Abbett model, i.e., the Mach disk location is determined by the coupling of the flow in the vicinity of the Mach disk with the reaccelerating transonic flow downstream of the disk. The present model is based on a local compatibility condition for the flow just downstream of the Mach disk. To evaluate the local compatibility condition, the generalized shape of the slip line which originates at the shock triple point must be known. The Abbett method was used to compute slip line geometries for a number of plume flows; correlation equations for the slip line geometrical parameters were then developed. After the Mach disk is located, the supersonic flow outside of the slip line is computed for the prescribed slip line geometry. The approximate analytical model requires relatively small computation times and yields acceptably accurate flow-field solutions over the range of conditions for which the slip line correlation equations are valid.