Author: William J. MontaPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
Book Description
Effect of Nose Bluntness on Transition for a Cone and a Hollow Cylinder at Mach Numbers 1.41 and 2.01
Author: William J. MontaPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
Book Description
Effect of Nose Bluntness on Transition for a Cone and a Hollow Cylinder at Mach Numbers 1.41 and 2.01
Author: William J. MontaEffect of Bluntness on Transition for a Cone and a Hollow Cylinder at Mach 3.1
Author: Paul F. BrinichPublisher:
ISBN:
Category : Cone
Languages : en
Pages : 42
Book Description
Bluntness was more effective in displacing transition downstream on a cylinder than on a cone. The downstream displacement of transition is related to the formation of a shock layer within which the Reynolds and Mach numbers are reduced and to pressure gradients that exist over the forward part of the model. Round bluntness in general had a favorable effect, whereas sharp-cornered flat bluntness above a certain size had unfavorable effects on the location of the transition point.
Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8
Author: P. Calvin StainbackPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
Book Description
Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1.57, 1.80, and 2.16 and Angles of Attack Up to 180 ̊
Author: David S. ShawPublisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 88
Book Description
Transonic Investigation of the Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Base Shape on the Static Aerodynamic Characteristics of Short, Blunt Cones at Angles of Attack to 1800
Author: Cuyler W. BrooksPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
Boundary-layer Transition on an Open-nose Cone at Mach 3.1
Author: Paul F. BrinichPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 11
Book Description
Bluntness effects on the open-nose cone were quite similar to those observed on the hollow cylinder. Transition was displaced downstream 2.2 times the sharp-cone transition distance by blunting the tip.
Effects of Cone Angle, Mach Number, and Nose Blunting on Transition at Supersonic Speeds
Author: K. R. CzarneckiEffect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8
Author: Calvin P. StainbackEffect of Unsymmetrical Nose-bluntness of the Pressure Distribution Over a 10° Cone at Mach-14
Author: Otto WalchnerPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 35
Book Description