Author: W. Frank StaylorPublisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 42
Book Description
Flow-field Investigation for Large-angle Cones with Short Spikes at a Mach Number of 9.6
Author: W. Frank StaylorPublisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 42
Book Description
Scientific and Technical Aerospace Reports
Author: An Experimental Investigation of the Flow Field Around a Yawed Cone
Author: Robert H. FeldhuhnPublisher:
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).
Aerodynamic Investigation of Sharp Cone-cylinder Spikes on 120 ̊blunted Cones at Mach Numbers of 3.00, 4.50, and 6.00
Author: Robert J. McGheePublisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 50
Book Description
Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95
Author: Jerome D. JuliusPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
Book Description
An Experimental Investigation of Supersonic Flow Past Circular Cones at High Angles of Attack
Author: Abdollah ModaviExperimental Determination of the Recovery Factor and Analytical Solution of the Conical Flow Field for a 20 ̊included Angle Cone at Mach Numbers of 4.6 and 6.0 and Stagnation Temperatures to 2600 ̊R
Author: Frank A. PfylPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
Book Description
Aerodynamic Characteristics of Towed Spheres, Conical Rings, and Cones Used as Decelerators at Mach Numbers from 1.57 to 4.65
Author: Nickolai CharczenkoPublisher:
ISBN:
Category : Cone
Languages : en
Pages : 88
Book Description
An investigation was made to determine the drag and stability characteristics of the various decelerators when towed in the wake of several space-vehicle configurations at Mach numbers from 1.57 to 4.65. The following parameters were varied: Reynolds number, trailling distance, ratio of deceleration base diameter to space-vehicle base diameter, cone angle, and size of disk added to the base of a cone.
Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90°
Author: Raul Jorge ContiPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
Book Description
Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
An Experimental Investigation of the Flow Field Around a Yawed Cone
Author: Robert H. FeldhuhnPublisher:
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).