Design Of A Supersonic Wind Tunnel For Mach Numbers 20 To 35 With Variable Second Throat
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Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section
Author | : Rudolf Hermann |
Publisher | : |
Total Pages | : 90 |
Release | : 1950 |
Genre | : Wind tunnels |
ISBN | : |
In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Handbook of Supersonic Aerodynamics
Author | : George Rudinger |
Publisher | : |
Total Pages | : 452 |
Release | : 1964 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Handbook of Supersonic Aerodynamics
Author | : Johns Hopkins University. Applied Physics Laboratory |
Publisher | : |
Total Pages | : 460 |
Release | : 1964 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Preliminary Investigation of a Variable Mach Number Two-dimensional Supersonic Tunnel of Fixed Geometry
Author | : William J. Nelson |
Publisher | : |
Total Pages | : 58 |
Release | : 1949 |
Genre | : Supersonic wind tunnels |
ISBN | : |
Wind Tunnel Designs and Their Diverse Engineering Applications
Author | : Noor Ahmed |
Publisher | : BoD – Books on Demand |
Total Pages | : 232 |
Release | : 2013-03-06 |
Genre | : Science |
ISBN | : 9535110470 |
This book is intended to be a valuable addition to students, engineers, scientists, industrialists, consultants and others providing greater insight into wind tunnel designs and their enormous research potential. It is a compilation of works from world experts on subsonic and supersonic wind tunnel designs, applicable to a diverse range of disciplines. The book is organised in two sections. The first section comprises of three chapters on various aspects of stationary and portable subsonic wind tunnel designs, followed by one chapter on supersonic wind tunnel and the final chapter discusses a method to address unsteadiness effects of fan blade rotation. The second section contains four chapters regarding wind tunnel applications across a multitude of engineering fields including civil, mechanical, chemical and environmental engineering.
A Method for the Design of Porous-wall Wind Tunnels
Author | : George M. Stokes |
Publisher | : |
Total Pages | : 60 |
Release | : 1956 |
Genre | : Boundary layer |
ISBN | : |
Supersonic Inlet Investigation
Author | : T. W. Tsukahira |
Publisher | : |
Total Pages | : 330 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Scientific and Technical Aerospace Reports
Author | : |
Publisher | : |
Total Pages | : 764 |
Release | : 1983 |
Genre | : Aeronautics |
ISBN | : |
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.