An Experimental Investigation of Supersonic Flow
Author : Joseph Francis Madden (Jr.)
Publisher :
Page : 46 pages
File Size : 39,84 MB
Release : 1941
Category :
ISBN :
Author : Joseph Francis Madden (Jr.)
Publisher :
Page : 46 pages
File Size : 39,84 MB
Release : 1941
Category :
ISBN :
Author : Malcom Green
Publisher :
Page : 78 pages
File Size : 36,62 MB
Release : 1951
Category :
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Author : Edward Malcolm Harvey Newton
Publisher :
Page : 100 pages
File Size : 42,30 MB
Release : 1964
Category : Aerodynamics, Supersonic
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Author : Robert Earl Wilson
Publisher :
Page : 110 pages
File Size : 36,4 MB
Release : 1966
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Author : Abdollah Modavi
Publisher :
Page : 286 pages
File Size : 35,34 MB
Release : 1978
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Author : Rafael Yahalom
Publisher :
Page : 148 pages
File Size : 14,42 MB
Release : 1971
Category : Wind tunnels
ISBN :
An experimental investigation of supersonic flow around cones was conducted at a free stream mach number of 2.72 and Reynolds number per foot of 1660000. Three cones of semi-apex angles of 10 deg, 15 deg, and 10 deg were investigated at relative incidences up to 3. In addition to measuring surface pressure, a detailed study of the flow in the plane of symmetry phi = 180 deg was made by means of a pitot-hot wire probe. The shape of the outer shock wave as well as of the imbedded shocks were determined. Oil and vapor screen techniques and a Schlieren system were used to visualize the flow field. (Author).
Author : H. Ronald Miller
Publisher :
Page : 144 pages
File Size : 14,83 MB
Release : 1962
Category :
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Author : Jain-Ming Wu
Publisher :
Page : 10 pages
File Size : 48,45 MB
Release : 1970
Category : Aerodynamics, Supersonic
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Author : W. E. Moeckel
Publisher :
Page : 56 pages
File Size : 26,67 MB
Release : 1950
Category : Aerodynamics, Supersonic
ISBN :
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 : E. V. Laitone
Publisher :
Page : 50 pages
File Size : 37,58 MB
Release : 1950
Category : Ultrasonic waves
ISBN :