Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Spanmissile with Three Wing Planforms PDF Download
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Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
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Book Description
Author: Earl D. Knechtel
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 36
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Book Description
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Author: Donald T. Gregory
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 34
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Book Description
Author: William A. Corlett
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 100
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Book Description
Transonic wind tunnel tests were conducted on a body of revolution with various fin configurations to investigate jet plume effects on missile longitudinal stability. A series of cold air normal jets located downstream of the base were utilized to simulate the jet plume. Fins of various planform geometry were tested at a forward longitudinal location only. The angle of attack range was -4 to 11 degrees at Mach numbers of from 0.2 to 2.3. The test was run at the Arnold Engineering Development Center Transonic (16T) and Supersonic (16S) wind tunnels and was designated AEDC SF172/TF360. (Author).
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724228208
Category :
Languages : en
Pages : 30
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Book Description
Longitudinal aerodynamic characteristics of a Sparrow 3 wing control missile model were measured through a range of separation distances relative to a flat plate surface that represented the parent-body configuration. Measurements were obtained with and without two dimensional circular arc protuberances attached to the flat plate surface. The tests were conducted at a Mach number of 2.86 and a Reynolds number per meter of 6.56 million. The behavior of these longitudinal characteristics with varying separation distance in the flow field created by the flat plate and protuberance was generally as would be expected on the basis of flow field boundaries determined from the second order approximation of Friedrich. In general, varying roll angle from 0 deg to 45 deg caused no significant effect on the store separation characteristics. Stallings, R. L., Jr. Langley Research Center NASA-TM-85713, L-15705, NAS 1.15:85713 RTOP 505-43-23-02
