Lanterna Rally
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Investigation of the Static Longitudinal Aerodynamic Characteristics of a 1/10-scale Model of the Blue Scout Jr. at Mach Numbers from 0.40 to 1.03
The Static Stability Characteristics of Several Preliminary Models of the X-15 Research Airplane at Mach Numbers of 2.98 and 4.01
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.
Investigation of the Aerodynamic Characteristics of Two Preliminary Designs of Scout Research Vehicle at Mach Numbers from 1.77 to 4.65
Aerodynamic Loading Characteristics of a 1/10-scale Model of the Three-stage Scout Vehicle at Mach Numbers 1.57 to 4.65
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.
Longitudinal Aerodynamic Characteristics of Several Fifth-stage Scout Reentry Vehicles from Mach Number 0.60 to 24.4 Including Some Reynolds Number Effects on Stability at Hypersonic Speeds
Aerodynamic Characteristics at a Mach Number of 3.10 of Several Fourth-stage Shapes of the Scout Research Vehicle
Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail
Author: M. Leroy Spearman
Publisher:
Published: 1957
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOK →An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
