Author: John T. McSheraPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 20
Book Description
Wind-tunnel Pressure Measurements in the Wake of a Cone-cylinder Model at Mach Numbers of 2.30 and 4.65
Author: John T. McSheraPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 20
Book Description
Wind-tunnel Measurements at Mach Numbers from 3 to 5 of Pressure and Turbulent Heat Transfer on a Blunt Cone-cylinder with Flared Afterbody
Author: Mamoru InouyeAn Experimental Study of the Turbulent Wake Behind a Cone at Mach 5
Author: William C. RagsdalePublisher:
ISBN:
Category : Turbulence
Languages : en
Pages : 166
Book Description
An experimental study of the turbulent wake behind a 9° adiabatic cone at Mach 5 has been carried out in the U.S. Naval Ordnance Laboratory Hypersonic Tunnel. Cone models with base diameters of 2 inches and 4 inches were mounted in the wind tunnel test section with fine wires. Pitot pressure, pressure on a small cone probe and total temperature were measured with probes mounted on a vertical traversing mechanism. The measured pressures and temperatures were used to calculate the Mach number, static pressure, static temperature, velocity and density in the wake.
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 670
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.
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
Investigation of Reynolds Number Effects for a Series of Cone-cylinder Bodies at Mach Number of 1.62, 1.93, and 2.41
Author: Carl E. GrigsbyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
Book Description
Abstract: An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having varying fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 106 to 10 x 106. The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number.
Pressure Distribution Measurements on Several Rigid Hyperflo Models at Mach 3.0 and 4.0
Author: R. A. NoreenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 95
Book Description
The internal and external surface pressures on rigid wind tunnel models of Hyperflo canopies of 5%, 10%, and 15% geometric porosity, with mesh and grid porous areas, were measured, and Schlieren flow photographs were taken. The measurements were conducted in a 12 in. x 12 in. supersonic wind tunnel in free-stream and in the wake of a cone-cylinder forebody at Mach numbers of 3.0 and 4.0 and Reynolds numbers/ft. from 860,000 to 2,990,000. (Author).
Wind-tunnel Pressure Data at Mach Numbers from 1.6 to 4.63 for a Series of Bodies of Revolution at Angles of Attack from -4 ̊to 60 ̊
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 156
Book Description
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.
Wind-tunnel Calibrations of a Combined Pitot-static Tube Vane-type Flow-direction Transmitter, and Stagnation-temperature Element at Mach Numbers from 0.60 to 2.87
Author: Norman R. RichardsonPublisher:
ISBN:
Category : Mach number
Languages : en
Pages : 30
Book Description