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: International Aerospace Abstracts
Author: Experimental Investigation of a Fin-cone Interference Flow Field at Mach 5
Author: Gillerlain, Jr. (Joseph D.)Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 86
Book Description
The general purpose of this investigation was to study the separated flow field associated with a fin-body juncture. Specific objectives included: (a) determining the severity and extent of aerodynamic heating, (b) providing flow visualization results to illustrate the flow structure, and (c) obtaining a data base of heat-transfer and surface-pressure measurements upon which to develop future analytical relations to predict peak interference heating levels. Tests were conducted at Mach 5 over a unit Reynolds number range of 4.5 to 26 million per foot. A fin-cone model was used. The data consist of surface- pressure distributions, heat-transfer measurements using the phase-change paint technique, and schlieren and oil-flow photographs. Results are presented for several fin-cone geometries to include fin sweep and fin-cone gap. Where possible, comparisons are made with fin-flat-plate data.
An Experimental Investigation of the Flow Field Around a Yawed Cone
Author: Robert H. FeldhuhnPublisher:
ISBN:
Category :
Languages : en
Pages : 0
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).
Flow Field Measurements Around an Ogive-cylinder at Angles of Attack Up to 15 Degrees for Mach Numbers 3.5 and 4
Author: William C. RagsdalePublisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 162
Book Description
The flow field was surveyed at one station (X/D = 6.5) on an ogive- cylinder having a tangent ogive nose with a fineness ratio of 4. The surveys were performed with pitot tubes and cone pressure probes at angles of attack of 0, 5, 10 and 15 degrees for Mach numbers 3.52 and 4.07. Surface static pressures were also measured. The results of the tests are presented in tabular and plotted form. Comparisons are made with inviscid flow fields calculations and with experimental results from other investigations.
Investigation of the Flow Over a Spiked-nose Hemisphere-cylinder at a Mach Number of 6.8
Author: Davis H. CrawfordPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 68
Book Description
Inlet Flowfield Investigation. Part 2: Computation of the Flow about a Supercruise Forebody at Supersonic Speeds
Author: Shock Waves
Author: Klaus HannemannPublisher: Springer Science & Business Media
ISBN: 3540851682
Category : Science
Languages : en
Pages : 810
Book Description
The 26th International Symposium on Shock Waves in Göttingen, Germany was jointly organised by the German Aerospace Centre DLR and the French-German Research Institute of Saint Louis ISL. The year 2007 marked the 50th anniversary of the Symposium, which first took place in 1957 in Boston and has since become an internationally acclaimed series of meetings for the wider Shock Wave Community. The ISSW26 focused on the following areas: Shock Propagation and Reflection, Detonation and Combustion, Hypersonic Flow, Shock Boundary Layer Interaction, Numerical Methods, Medical, Biological and Industrial Applications, Richtmyer Meshkov Instability, Blast Waves, Chemically Reacting Flows, Diagnostics, Facilities, Flow Visualisation, Ignition, Impact and Compaction, Multiphase Flow, Nozzles Flows, Plasmas and Propulsion. The two Volumes contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 26 and individuals interested in these fields.
Supersonic Flow about Cones at Large Angles of Attack
Author: Clive Allen John FletcherPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 294
Book Description
A numerical method is presented which is applicable to the supersonic inviscid flow about cones inclined at such angles of attack that a substantial region of supersonic crossflow exists (M sub cr 1). The method is based partly on the method of Gilinskii, Telenin and Tinyakov and partly on the method of characteristics. The method produces results that compare favorably with experimental data and with the results of other numerical methods. The numerical method has produced results in the range: free stream Mach number =3 to 16; incidence, alpha = 10 to 50 deg, nose cone angles, theta sub b = 5 to 30 deg. These results demonstrate similar trends with free stream Mach number, alpha and theta sub b as obtained for subsonic crossflow Mach numbers (m sub cr