The Design And Development Of A Mach 4 Supersonic Wind Tunnel
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Author | : Bradley G. DeBlauw |
Publisher | : |
Total Pages | : 338 |
Release | : 2008 |
Genre | : |
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Download The Design and Development of a Mach 4 Supersonic Wind Tunnel Book in PDF, Epub and Kindle
Author | : John Russell Radbill |
Publisher | : |
Total Pages | : 88 |
Release | : 1955 |
Genre | : |
ISBN | : |
Download Design of an Inexpensive Supersonic Wind Tunnel with an Inlet Mach Number of Five for Heat Transfer Studies Book in PDF, Epub and Kindle
Author | : Peter Ashurkoff |
Publisher | : |
Total Pages | : 170 |
Release | : 1954 |
Genre | : |
ISBN | : |
Download Design of a Small Supersonic Wind Tunnel for Heat Transfer Measurements at Mach Five Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 36 |
Release | : 1948 |
Genre | : Supersonic wind tunnels |
ISBN | : |
Download The High-speed Flexible-throat Supersonic Wind Tunnel Book in PDF, Epub and Kindle
Author | : Rudolf Hermann |
Publisher | : |
Total Pages | : 90 |
Release | : 1950 |
Genre | : Wind tunnels |
ISBN | : |
Download Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section Book in PDF, Epub and Kindle
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.
Author | : Armen Melikian |
Publisher | : |
Total Pages | : 90 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download Design of a Supersonic Wind Tunnel for Mach Numbers 2.0 to 3.5 with Variable Second Throat Book in PDF, Epub and Kindle
Author | : George M. Stokes |
Publisher | : |
Total Pages | : 60 |
Release | : 1956 |
Genre | : Boundary layer |
ISBN | : |
Download A Method for the Design of Porous-wall Wind Tunnels Book in PDF, Epub and Kindle
Author | : Euell Clay Anderson |
Publisher | : |
Total Pages | : 144 |
Release | : 1962 |
Genre | : Supersonic wind tunnels |
ISBN | : |
Download The Design of a 3.4 by 3.4 Inch Supersonic Wind Tunnel Capable of Continuous Operation in the Range of Mach Numbers Between 1.50 and 3.59 Book in PDF, Epub and Kindle
Author | : N. A. Ahmed |
Publisher | : |
Total Pages | : |
Release | : 2013 |
Genre | : Science |
ISBN | : |
Download Design and Development of a Gas Dynamics Facility and a Supersonic Wind Tunnel Book in PDF, Epub and Kindle
Design and Development of a Gas Dynamics Facility and a Supersonic Wind Tunnel.
Author | : L. E. Leavy |
Publisher | : |
Total Pages | : 31 |
Release | : 1956 |
Genre | : Supersonic wind tunnels |
ISBN | : |
Download A Supersonic Wind Tunnel for Mach Numbers Up to 3.5 Book in PDF, Epub and Kindle