Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.16 of a Blunt-nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins PDF Download
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Author: William J. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Author: William J. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Author: William A. Corlett
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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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: Jimmie N. Derrick
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 896
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Book Description
Wind tunnel tests were conducted in a 16 ft. transonic tunnel, a supersonic tunnel, A and a trisonic tunnel to establish a bank of systematic data for body and body-tail configurations at high angles of attack. The configurations were tested at Mach numbers between 0.8 and 3.0, angles of attack from -2 to 45 degrees, and roll angles from 0 to 90 degrees. The aerodynamic characteristics were obtained for the total configuration as well as each of the four undeflected tail fins.
Author: Robert J. Keynton
Publisher:
ISBN:
Category : Aircraft
Languages : en
Pages : 60
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Book Description
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.
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
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Book Description
Author: D.K. Smith
Publisher:
ISBN:
Category : Cylinders
Languages : en
Pages : 166
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Book Description
Author: David S. Shaw
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 88
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Book Description
Author: Howard F. Savage
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 662
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Book Description
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
