Author: Harold N. RiisePublisher:
ISBN:
Category :
Languages : en
Pages : 41
Book Description
Flexible-plate Nozzle Design for Two-dimensional Supersonic Wind Tunnels
Author: Harold N. RiiseDesign and Operation of a Continuous-flow Hypersonic Wind Tunnel Using a Two-dimensional Nozzle
Author: Harris M. SchurmeierPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 304
Book Description
A Flexible Plate Nozzle Design for an Operating Mach Number Range of 1.4 to 2.0
Author: Terence G. EmmertPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The design for a supersonic flexible plate nozzle is presented. The nozzle was required for a supersonic blow-down cascade wind tunnel facility at the Naval Postgraduate School's Gas Dynamics Laboratory. Overall dimensions were based on calculations of the required test section height and width which would give acceptable (2 minute) mn times over an operating Mach number range from 1.4 to 2.0. A two-dimensional, constant-plate thickness, multiple-jack screw configuration was the concept used to effect the nozzle geometry changes. Mention is made of a multi-disciplinary design optimization routine which helped to mle out a single-jack, variable-plate thickness configuration. The aerodynamic and structural analysis used in the design process is presented in detail. Preliminary drawings of the nozzle mechanism are included.
A Flexible Plate Nozzle Design for an Operating Mach Number Range of 1.4 to 2.0
Author: Terence G. EmmertPublisher:
ISBN:
Category :
Languages : en
Pages : 166
Book Description
The design for a supersonic flexible plate nozzle is presented. The nozzle was required for a supersonic blow-down cascade wind tunnel facility at the Naval Postgraduate School's Gas Dynamics Laboratory. Overall dimensions were based on calculations of the required test section height and width which would give acceptable (2 minute) mn times over an operating Mach number range from 1.4 to 2.0. A two-dimensional, constant-plate thickness, multiple-jack screw configuration was the concept used to effect the nozzle geometry changes. Mention is made of a multi-disciplinary design optimization routine which helped to mle out a single-jack, variable-plate thickness configuration. The aerodynamic and structural analysis used in the design process is presented in detail. Preliminary drawings of the nozzle mechanism are included.
Handbook of Supersonic Aerodynamics
Author: George RudingerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 452
Book Description
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics LaboratoryPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 460
Book Description
Supersonic Wind Tunnel Nozzles
Author: Stephen W. D. WolfPublisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 88
Book Description
Publications of the Jet Propulsion Laboratory, January 1938 Through June 1961
Author: D. K. Walsh2D Supersonic Nozzle Design
Author: Michael GoingPublisher:
ISBN:
Category :
Languages : en
Pages : 10
Book Description
In this paper, a method based on the theory of characteristics is presented for two-dimensional, supersonic nozzle design. Individual nozzle configurations for different applications are obtained by combining the geometric attributes of the symmetric, single expansion ramp, and Prandtl-Meyer type expansion nozzles. Corresponding to the design criteria, such as minimum length and optimum thrust efficiency, relations between desired properties of the flow field and nozzle geometry parameters are found, and a family of length-optimized, two-dimensional, supersonic nozzles is defined. The method can be applied for the design of wind tunnel and steam turbine nozzles as well as for thrust nozzle design of high Mach number aircraft.
Analytic Determination of Two-dimensional Supersonic Nozzle Contours Having Continuous Curvature
Author: James C. SivellsPublisher:
ISBN:
Category : Curvature
Languages : en
Pages : 29
Book Description
An analytic method is presented for determining the contours of two-dimensional supersonic nozzles having continuous curvature. The continuity of curvature is necessary for flexible-plate type nozzles inasmuch as the aerodynamic contour must be such that it can be closely simulated by the elastic curve of the flexible plate. The method described is more accurate and less time consuming than the characteristics method of obtaining contours. The assumption is made that radial flow can be obtained at the inflection point through the use of a simple polynomial for the initial part of the contour. This radial flow is converted to parrallel flow at the test section Mach number as described herein.