Wind Tunnel Tests of the Redstone "B" Nose Cone at Mach Numbers from 1.75 to 5.00 PDF Download
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Author: Maurice A. Sylvester
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 44
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Book Description
Author: Maurice A. Sylvester
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 44
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Book Description
Author: J. S. Hahn
Publisher:
ISBN:
Category : Ablation (Aerothermodynamics)
Languages : en
Pages : 262
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Book Description
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 110
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Book Description
Author: John P. Jr Mugler
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Book Description
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
Author: Frederick B. Cyran
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
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Book Description
Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 0
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Book Description
Author: Carroll B. Butler
Publisher:
ISBN:
Category : Radomes
Languages : en
Pages : 248
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Book Description
This report summarizes wind tunnel test data on various body alone configurations which provide a data matrix for bluff and pointed bodies of revolution with systematic variations in nose bluffness, nose fineness ratio, and cylinder afterbody fineness ratio. Modular model components were used to obtain static stability and drag data, with emphasis on the effect of nose bluffness on drag. Although data is included for tangent ogive noses of fineness ratio 2, 2.25, 2.5, 3.0, and 4, the nose fineness ratios of 2, 3, and 4 calibers include a systematic variation in nose bluffness ratios of 0.00, 0.25, 0.50, and 0.75 on cylindrical midsections of 5, 7, 9, and 11 calibers. A 1-caliber cylindrical afterbody is used with all configurations in this report.
