Lanterna Rally
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Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Fixed-span Missile with Three Wing Planforms
Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing
Longitudinal Aerodynamic Characteristics of Several High-drag Bodies at Mach Numbers from 1.50 to 4.63
Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20
Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4
Author: Earl D. Knechtel
Publisher:
Published: 1956
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOK →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.
Longitudinal and Lateral-directional Aerodynamic Characteristics of a Wing-cone Configuration at Mach Numbers from 2.5 to 4.5
Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63
Author: Robert J. Keynton
Publisher:
Published: 1971
Total Pages: 60
ISBN-13:
DOWNLOAD EBOOK →Results are presented of an experimental investigation to determine the static longitudinal aerodynamic characteristics of a fin with an enlarged tip control and the hinge-moment coefficients of the enlarged tip control. The model was tested at angles of attack from -6 [degree] to 6 [degree] and fin tip control deflections from -20° to 20°. A 1/8-scale model of the Scout first stage, with a tangent ogive nose, was used for these tests. Basic data obtained include the pitching-moment, rolling-moment, and normal-force coefficients of the fin and the hinge-moment coefficient of the enlarged tip control.
Aerodynamic Characteristics of a Sparrow 3 Missile Model in the Flow Field of a Generalized Parent Body at Mach 2. 86
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-25
Total Pages: 30
ISBN-13: 9781724228208
DOWNLOAD EBOOK →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
