Supersonic Flow Over Flaps With Uniform Heat Transfer

Advances in Heat Transfer

The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.

Modelling and Computation of Turbulent Flows has been written by one of the most prolific authors in the field of CFD. Professor of aerodynamics at SUPAERO and director of DMAE at ONERA, the author calls on both his academic and industrial experience when presenting this work. The field of CFD is strongly represented by the following corporate companies; Boeing; Airbus; Thales; United Technologies and General Electric, government bodies and academic institutions also have a strong interest in this exciting field. Each chapter has also been specifically constructed to constitute as an advanced textbook for PhD candidates working in the field of CFD, making this book essential reading for researchers, practitioners in industry and MSc and MEng students. * A broad overview of the development and application of Computational Fluid Dynamics (CFD), with real applications to industry* A Free CD-Rom which contains computer program’s suitable for solving non-linear equations which arise in modeling turbulent flows* Professor Cebeci has published over 200 technical papers and 14 books, a world authority in the field of CFD

The major effort concerned with this project concerned the development of a small high stagnation temperature intermittant-flow supersonic wind tunnel and a description of this work and the resulting facility is presented. The development of an electrically heated shield temperature probe, for measurements of supersonic flow, is described and the results of an interference study, concerning total pressure probes in the boundary layer, are presented. Heat transfer measurements on a flat-plate model were accomplished and this ivestigation is described including a brief discussion of the test results. An analytical study concerning the temperature distribution through the turbulent boundary layer is also discussed. All of this work has been previously reported in considerable detail and specific references are given in each case.