Experimental Investigation of Supersonic Flow with Detached Shock Waves for Mach Numbers Between 1.8 and 2.9 PDF Download
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Author: W. E. Moeckel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
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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.
Author: W. E. Moeckel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
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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.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author: E. V. Laitone
Publisher:
ISBN:
Category : Ultrasonic waves
Languages : en
Pages : 50
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Author: Arthur Earl Bryson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 106
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Book Description
Interferometer measurements are given of the flow fields near two-dimensional wedge and circular-arc sections at zero angle of attack. Pressure distributions and drag coefficients as functions of Mach number were obtained and the wedge data are compared with theory. It is shown that the local Mach number at any point on the surface of a finite three dimensional body or an unswept two-dimensional body, moving through an infinite fluid, has a stationary value at Mach number 1 and, in fact, remains nearly constant for a range of speeds below and above Mach number 1. On the basis of this concept and the experimental data, pressure distributions and drag coefficients for the wedge and circular-arc sections are presented throughout the entire transonic range of velocities.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
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.
Author: Arthur Earl Bryson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 340
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Book Description
Author: E. R. G. Eckert
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 330
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Book Description
