Hypersonic Vehicle Design Using Inward Turning Flowfields
Author : Ajay P. Kothari
Publisher :
Page : pages
File Size : 39,11 MB
Release : 1996
Category :
ISBN :
Author : Ajay P. Kothari
Publisher :
Page : pages
File Size : 39,11 MB
Release : 1996
Category :
ISBN :
Author : Giuseppe Pezzella
Publisher : BoD – Books on Demand
Page : 150 pages
File Size : 20,93 MB
Release : 2019-10-02
Category : Science
ISBN : 1839622695
In the aviation field there is great interest in high-speed vehicle design. Hypersonic vehicles represent the next frontier of passenger transportation to and from space. However, several design issues must be addressed, including vehicle aerodynamics and aerothermodynamics, aeroshape design optimization, aerodynamic heating, boundary layer transition, and so on. This book contains valuable contributions focusing on hypervelocity aircraft design. Topics covered include hypersonic aircraft aerodynamic and aerothermodynamic design, especially aeroshape design optimization, computational fluid dynamics, and scramjet propulsion. The book also discusses high-speed flow issues and the challenges to achieving the dream of affordable hypersonic travel. It is hoped that the information contained herein will allow for the development of safe and efficient hypersonic vehicles.
Author :
Publisher :
Page : 13 pages
File Size : 33,28 MB
Release : 2007
Category :
ISBN :
A family of dual-axis compression, high-contraction-ratio, inward-turning inlets has been designed to achieve a desired shock structure and aerodynamic performance at Mach 6. Computational simulations of the internal inlet flowfield were performed using the research code FDL3DI. These solutions are an integrated part of the inlet design methodology and offer insight into the fundamental fluid phenomenology. The effects of viscous/inviscid interactions, namely swept-shock/turbulent boundary layer interactions are discussed. Additionally, the importance of complementary computational fluid dynamics (CFD) to the experimental work as part of the integrated hypersonic inlet design process is also addressed.
Author : Xinguo Zhang
Publisher : Springer
Page : 3091 pages
File Size : 22,97 MB
Release : 2019-06-08
Category : Technology & Engineering
ISBN : 981133305X
This book is a compilation of peer-reviewed papers from the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). The symposium is a common endeavour between the four national aerospace societies in China, Australia, Korea and Japan, namely, the Chinese Society of Aeronautics and Astronautics (CSAA), Royal Aeronautical Society Australian Division (RAeS Australian Division), the Korean Society for Aeronautical and Space Sciences (KSAS) and the Japan Society for Aeronautical and Space Sciences (JSASS). APISAT is an annual event initiated in 2009 to provide an opportunity for researchers and engineers from Asia-Pacific countries to discuss current and future advanced topics in aeronautical and space engineering.
Author :
Publisher :
Page : 740 pages
File Size : 31,35 MB
Release : 1996
Category : Airplanes
ISBN :
Author : Ernst Heinrich Hirschel
Publisher : Springer Science & Business Media
Page : 512 pages
File Size : 45,35 MB
Release : 2009-11-26
Category : Technology & Engineering
ISBN : 354089974X
In this book selected aerothermodynamic design problems in hypersonic vehicles are treated. Where applicable, it emphasizes the fact that outer surfaces of hypersonic vehicles primarily are radiation-cooled, an interdisciplinary topic with many implications.
Author : M. Costanzi
Publisher : Persiani Editore
Page : 736 pages
File Size : 34,24 MB
Release : 2021
Category : Technology & Engineering
ISBN :
The 2019 AIDAA Congress is the biennial Congress of the Italian Association of Aeronautics and Astronautics, the Italian no-profit cultural association dedicated to the aerospace community. AIDAA was formed in 1969 through a merging of the former Societies AIDA (Associazione Italiana di Aerotecnica formed in 1920) and AIR (Associazione Italiana Razzi).In 1951, AIDA was among the founders of the International Astronautical Federation (IAF) and in 1957 of the International Council of Aeronautical Sciences (ICAS). In 1992 AIDAA joined the Confederation of European Aerospace Societies (CEAS).The Congress is jointly hosted by AIDAA Rome Section, the Departments of Astronautic, Electric and Energetic Engineering (DIAEE) and of Mechanical and Aerospace Engineering (DIMA) of Civil and Industrial Engineering Faculty and the School of Aerospace Engineering (SIA) of Sapienza University of Rome. The degree courses in Aerospace Engineering are attended by almost 1500 students.
Author :
Publisher :
Page : 0 pages
File Size : 28,23 MB
Release : 1996
Category :
ISBN :
Here, we present the Final Technical Report on AASERT Grant No. F49620-93-1-0476 Studies of Hypersonic Vehicle Flowfields, in support of AFOSR Grant F49620-93-0064 'Studies Of Hypersonic Boundary Layer Behavior'. The parent grant covered three interrelated research efforts: a study of the structure of hypersonic turbulent boundary layers and shock wave boundary layer interactions, a study of boundary layer transition at supersonic and hypersonic speeds, and the development and application of new optical techniques including filtered Rayleigh scattering and RELIEF to obtain multi-dimensional velocity and density data in the supersonic and hypersonic regimes.
Author :
Publisher :
Page : 636 pages
File Size : 49,22 MB
Release : 1999
Category : Aeronautics
ISBN :
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 68 pages
File Size : 33,37 MB
Release : 2018-07-08
Category :
ISBN : 9781722313586
The geometric data of the generic hypersonic vehicle configuration included body definitions and preliminary grids for the forebody (nose cone excluded), midsection (propulsion system excluded), and afterbody sections. This data was to be augmented by the nose section geometry (blunt conical section mated with the noncircular cross section of the forebody initial plane) along with a grid and a detailed supersonic combustion ramjet (scramjet) geometry (inlet and combustor) which should be merged with the nozzle portion of the afterbody geometry. The solutions were to be obtained by using a Navier-Stokes (NS) code such as TUFF for the nose portion, a parabolized Navier-Stokes (PNS) solver such as the UPS and STUFF codes for the forebody, a NS solver with finite rate hydrogen-air chemistry capability such as TUFF and SPARK for the scramjet and a suitable solver (NS or PNS) for the afterbody and external nozzle flows. The numerical simulation of the hypersonic propulsion system for the generic hypersonic vehicle is the major focus of this entire work. Supersonic combustion ramjet is such a propulsion system, hence the main thrust of the present task has been to establish a solution procedure for the scramjet flow. The scramjet flow is compressible, turbulent, and reacting. The fuel used is hydrogen and the combustion process proceeds at a finite rate. As a result, the solution procedure must be capable of addressing such flows. Narayan, Johnny R. Unspecified Center...