Author: Gary L. Barr
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 118
Book Description
Experimental Investigation of the Sudden Expansion of Supersonic Flow Into a 90 ̊vee Shaped Channel
Author: Gary L. Barr
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 118
Book Description
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 118
Book Description
An Experimental Investigation of Supersonic Flow in Long Channels
Author: Malcom Green
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Book Description
An Experimental Investigation of Boundary Layer Expansion Around a Convex Corner in Supersonic Flow
Author: Thomas Johani
Publisher:
ISBN:
Category :
Languages : en
Pages : 142
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 142
Book Description
Experimental Investigation of Supersonic Flow with Detached Shock Waves for Mach Numbers Between 1.8 and 2.9
Author: W. E. Moeckel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
Book Description
Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
Book Description
Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.
Experimental Investigation of Normal, Sonic Injection Through a Wedge-shaped Nozzle Into Supersonic Flow
Author: Matthew James Barber
Publisher:
ISBN:
Category : Acoustical engineering
Languages : en
Pages : 392
Book Description
Publisher:
ISBN:
Category : Acoustical engineering
Languages : en
Pages : 392
Book Description
An Experimental Investigation of Transonic and Accelerated Supersonic Flow by the Hydraulic Analogy
Author: E. V. Laitone
Publisher:
ISBN:
Category : Ultrasonic waves
Languages : en
Pages : 50
Book Description
Publisher:
ISBN:
Category : Ultrasonic waves
Languages : en
Pages : 50
Book Description
Supersonic Sudden-expansion Flow with Fluid Injection
Author: S.M. Correa
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
An Experimental Investigation of Separated Turbulent Supersonic Flow at M
Author: Robert Earl Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 110
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 110
Book Description
Experimental Study of the Supersonic Flow Around V-Shaped Wings
Author: A. L. Gonor
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1090
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1090
Book Description