An Experimental Investigation of the Flow Field Around a Yawed Cone PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download An Experimental Investigation of the Flow Field Around a Yawed Cone PDF full book. Access full book title An Experimental Investigation of the Flow Field Around a Yawed Cone by Robert H. Feldhuhn. Download full books in PDF and EPUB format.
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Cone Languages : en Pages : 106
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Cone Languages : en Pages : 106
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Languages : en Pages : 79
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Rafael Yahalom Publisher: ISBN: Category : Wind tunnels Languages : en Pages : 148
Book Description
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: Edward M. Schmidt Publisher: ISBN: Category : Languages : en Pages : 44
Book Description
The paper presents the results of an experimental survey of the flow field around a sharp, 10 degree half angle cone. Tests were conducted at a free stream Mach number of 7.7 for a range of free stream Reynolds numbers of 110,000 to 171,000 per foot. Surface heat transfer data indicates that the cone boundary layer varies from laminar to fully developed turbulent over this Reynolds number range. The base pressure variation was also obtained throughout this range of Reynolds numbers; from this, the interrelation between the surface boundary layer properties and the base pressure is discussed. A series of tests were conducted in the near wake region at two different values of free stream Reynolds number, i.e., 330,000 and 1,650,000 per foot, corresponding to a completely laminar and fully developed turbulent surface boundary layer at the cone shoulder, respectively. The relationship between boundary layer properties and near wake properties is studied. (Author).
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 580
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author: Robert H. Feldhuhn
Author: Robert H. Feldhuhn
Author: Robert H. Feldhuhn
Author: Rafael Yahalom
Author: Edward M. Schmidt
Author: 
Author: Tōkyō Daigaku. Kōkū Kenkyūjo
Author: 
Author: Woo Taik Moon
Author: 
Author: