Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors PDF Download

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Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors

Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors PDF Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64

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Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors

Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors PDF Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64

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Book Description

Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63

Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63 PDF Author: Clarence A. Brown
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 86

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Aerodynamic Characteristics in Pitch of a 1/7-scale Model of a Two- and Three-stage Rocket Configuration at Mach Numbers of 0.4 to 4.63

Aerodynamic Characteristics in Pitch of a 1/7-scale Model of a Two- and Three-stage Rocket Configuration at Mach Numbers of 0.4 to 4.63 PDF Author: William F. Hinson
Publisher:
ISBN:
Category : Pitching (Aerodynamics)
Languages : en
Pages : 52

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Book Description
Aerodynamic characteristics in pitch of scale model of two and three stage rocket configuration at Mach numbers of 0.4 to 4.63.

Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0.065-scale Model of a Four-stage Rocket Configuration at Mach Numbers of 1.41 and 1.82

Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0.065-scale Model of a Four-stage Rocket Configuration at Mach Numbers of 1.41 and 1.82 PDF Author: Ross B. Robinson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 38

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Transonic Wind-tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Several Configurations of the Scout Vehicle and of a Number of Related Models

Transonic Wind-tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Several Configurations of the Scout Vehicle and of a Number of Related Models PDF Author: Thomas C. Kelly
Publisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 74

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Book Description
Results have been obtained i n t h e Langley 8-foot transonic pressure tunnel at Mach numbers from 0.40 t o 1.20 for several configurations of the Scout vehicle and f o r a number of related models. Tests extended over an angle-of-attack range from about -10 degrees to 10 degrees at a Reynolds number per foot of about 3.8 x 10 sup 6.

A Summary of Jet Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0.2 to 2.3

A Summary of Jet Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0.2 to 2.3 PDF Author: George Batiuk
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 194

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Book Description
This report summarizes the studies made to date by the Army Missile Command on the effects of the rocket jet plume on the Stability characteristics of a body of revolution with various fin configurations and at various fin positions on the body. The Mach numbers ranged from 0.2 to 2.3. A normal jet plume simulator was used to obtain the desired plume effects. This report concerns itself with those tests conducted on a 5-in. diameter, 52-in. long model, with a 3 caliber tangent ogive nose.

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

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 Author: William J. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36

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Supersonic Aerodynamic Characteristics of a 1/6-scale Model of the Final Two Stages of the Argo D-4 Four-stage Rocket Vehicle

Supersonic Aerodynamic Characteristics of a 1/6-scale Model of the Final Two Stages of the Argo D-4 Four-stage Rocket Vehicle PDF Author: Clyde Hayes
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4

Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4 PDF 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.

An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4

An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 PDF Author: Calvin Wayne Dahlke
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 200

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Book Description
The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).