Design Of A Small Supersonic Wind Tunnel For Heat Transfer Measurements At Mach Five
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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 | : 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 | : Joseph Kaye |
Publisher | : |
Total Pages | : 23 |
Release | : 1954 |
Genre | : Boundary layer |
ISBN | : |
Download An Inexpensive Supersonic Wind Tunnel for Heat-transfer Measurements Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 52 |
Release | : 1980 |
Genre | : |
ISBN | : |
Download Wind-tunnel Measurements and Comparison with Flight of the Boundary Layer and Heat Transfer on a Hollow Cylinder at Mach 3 Book in PDF, Epub and Kindle
Author | : K. W. Nutt |
Publisher | : |
Total Pages | : 82 |
Release | : 1985 |
Genre | : |
ISBN | : |
Download Analysis of Heat-Transfer Measurements from Two AEDC Wind Tunnels on the Shuttle External Tank Book in PDF, Epub and Kindle
Previous aerodynamic heating tests were conducted in the AEDC/VKF Supersonic Wind Tunnel (A) to aid in defining the design thermal environment for the Space Shuttle external tank. The quality of these data has been under discussion because of the effects of low tunnel enthalpy and slow model-injection rates. Recently the AEDC/VKF Hypersonic Wind Tunnel (C) was modified to provide a Mach 4 capability that has significantly higher tunnel enthalpy with more rapid model-injection rates. Tests were conducted in Tunnel C at Mach 4 to obtain data on the external tank for comparison with Tunnel A results. Data were obtained on a 0.0175-scale model of the Space Shuttle Integrated Vehicle at Re/ft = 4 million with the tunnel stagnation temperature varying from 740 to 1440 R. Model attitude varied from an angle of attack of -5 to 5 deg and an angle of sideslip of -3 to 3 deg. One set of data was obtained in Tunnel C at Re/Ft = 69 million for comparison with flight data. This report presents data comparisons betwen the two tunnels for numerous regions on the external tank. Tunnel-to-flight data comparisons are presented for a small number of locations on the nose of the external tank. Keywords: Heat transfer; Mach number; Reynolds number; Aerodynamic heating; Wind tunnel tests; Aerothermodynamics; Enthalpy.
Author | : Hsieh-Hsiang Sam Chiu |
Publisher | : |
Total Pages | : |
Release | : 1999 |
Genre | : Heat |
ISBN | : |
Download Heat Transfer Measurements Using Narrow-band Liquid Crystals in a Supersonic Blowdown Wind Tunnel Book in PDF, Epub and Kindle
Author | : Ruth N. Weitmann |
Publisher | : |
Total Pages | : 36 |
Release | : 1962 |
Genre | : Chemistry, Physical and theoretical |
ISBN | : |
Download Design and Calibration of an Arc-heated, Hypersonic, Low-density Wind Tunnel Book in PDF, Epub and Kindle
Author | : Robert L. Stallings |
Publisher | : |
Total Pages | : 52 |
Release | : 1980 |
Genre | : Aerothermodynamics |
ISBN | : |
Download Wind-tunnel Measurements and Comparison with Flight of the Boundary Layer and Heat Transfer on a Hollow Cylinder at Mach 3 Book in PDF, Epub and Kindle
Author | : Noor Ahmed |
Publisher | : BoD – Books on Demand |
Total Pages | : 232 |
Release | : 2013-03-06 |
Genre | : Science |
ISBN | : 9535110470 |
Download Wind Tunnel Designs and Their Diverse Engineering Applications Book in PDF, Epub and Kindle
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.
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.