Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Scientific and Technical Aerospace Reports
Author: U.S. Government Research Reports
Author: U.S. Government Research Reports
Author: Wind Tunnel Designs and Their Diverse Engineering Applications
Author: Noor AhmedPublisher: BoD – Books on Demand
ISBN: 9535110470
Category : Science
Languages : en
Pages : 232
Book Description
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.
Proceedings of a Short Course on "Noise Generation and Suppression in Aircraft," Held at the University of Tennessee Space Institute, Tullahoma, Tennessee, January 29-February 2, 1968
Author: University of Tennessee (Knoxville campus). Space InstitutePublisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 666
Book Description
NASA Technical Memorandum
Author: Investigation of Flow Separation on a Two-dimensional Flat Plate Haveing a Variable-san Trailing-edge Flap at M [free Stream]
![Investigation of Flow Separation on a Two-dimensional Flat Plate Haveing a Variable-san Trailing-edge Flap at M [free Stream] PDF](https://books.google.com/books/content/images/frontcover/EivnMbfPiHMC?fife=w80-h100)
Author: S. R. PatePublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 46
Book Description
An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailing edge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.
Author: 
Author: 
Author: