An Experimental Investigation of the Aerodynamic Characteristics of Slender Hypersonic Vehicles at High Angles of Attack PDF Download
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Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 148
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Book Description
Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 148
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Book Description
Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category :
Languages : en
Pages : 119
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Book Description
Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 106
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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).
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 82
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Book Description
An experimental investigation illustrating some separated flow phenomena associated with highly inclined circular cones was conducted at a nominal Mach number of 5 and at nominal free stream Reynolds numbers per foot of 4,800,000. Surface static pressure measurements, Pitot pressure surveys, schlieren photographs, vapor screen photographs, and surface sublimation measurements were obtained on a sharp 5 degree semi-vertex angle cone at angles of attack up to 40 degrees. The static pressure distribution along the most leeward meridian generator was found to be dependent upon the Reynolds number based upon the distance from the vertex of the cone. The vapor screen photographs at 40 degrees angle of attack indicate the existence of imbedded shock waves in the flow field on the leeward side of the cone. The Pitot tube surveys and the surface sublimation photographs indicate the existence of a region of attached flow near the leeward meridian plane. The surface sublimation photographs also indicate the possible existence of a secondary vortex. (Author).
Author:
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ISBN:
Category : Nuclear energy
Languages : en
Pages : 78
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 818
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722219161
Category :
Languages : en
Pages : 38
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Book Description
An extensive series of ballistic range tests were conducted at the Ames Research Center to determine precisely the aerodynamic characteristics of the Galileo entry probe vehicle. Figures and tables are presented which summarize the results of these ballistic range tests. Drag data were obtained for both a nonablated and a hypothesized ablated Galileo configuration at Mach numbers from about 0.7 to 14 and at Reynolds numbers from 1000 to 4 million. The tests were conducted in air and the experimental results were compared with available Pioneer Venus data since these two configurations are similar in geometry. The nonablated Galileo configuration was also tested with two different center-of-gravity positions to obtain values of pitching-moment-curve slope which could be used in determining values of lift and center-of-pressure location for this configuration. The results indicate that the drag characteristics of the Galileo probe are qualitatively similar to that of Pioneer Venus, however, the drag of the nonablated Galileo is about 3 percent lower at the higher Mach numbers and as much as 5 percent greater at transonic Mach numbers of about 1.0 to 1.5. Also, the drag of the hypothesized ablated configuration is about 3 percent lower than that of the nonablated configuration at the higher Mach numbers but about the same at the lower Mach numbers. Additional tests are required at Reynolds numbers of 1000, 500, and 250 to determine if the dramatic rise in drag coefficient measured for Pioneer Venus at these low Reynolds numbers also occurs for Galileo, as might be expected. Intrieri, Peter F. Unspecified Center NCC2-475...
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 794
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
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Book Description
