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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 Rocket Vehicle with Thick Wedge Fins and Sweptback Leading and Trailing Edges
Author: Joseph A. Yuska
Publisher:
Published: 1966
Total Pages: 20
ISBN-13:
DOWNLOAD EBOOK →The longitudinal static stability characteristics of three one-fifth scale models of the second stage of a sounding rocket were calculated and compared with the measured values at Mach numbers of 1.79 to 3.47. All three models had fins of trapezoidal planform with sweptback leading and trailing edges, small aspect ratio, and thick wedge sections, but differed in fin area and overall model length. Calculation of center of pressure and normal-force coefficient slope at zero normal force were in good agreement with experimental data.
Static Stability Investigation of a Sounding-rocket Vehicle at Mach Numbers from 1.50 to 4.63
Aerodynamic Characteristics from Mach 0.22 to 4.65 of a Two-stage Rocket Vehicle Having an Unusual Nose Shape
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
Author: William F. Hinson
Publisher:
Published: 1969
Total Pages: 52
ISBN-13:
DOWNLOAD EBOOK →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
Transonic Wind-tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Several Configurations of the Scout Vehicle and of a Number of Related Models
Author: Thomas C. Kelly
Publisher:
Published: 1961
Total Pages: 74
ISBN-13:
DOWNLOAD EBOOK →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
Author: George Batiuk
Publisher:
Published: 1976
Total Pages: 194
ISBN-13:
DOWNLOAD EBOOK →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.
Supersonic Aerodynamic Characteristics of a 1/6-scale Model of the Final Two Stages of the Argo D-4 Four-stage Rocket Vehicle
