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
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

Author: Thomas C. Kelly

Publisher:

Published: 1962

Total Pages: 1

ISBN-13:

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Results were obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.40 to 1.03 for a 1/10-scale model of the Blue Scout Jr. Tests extended over an angle-of-attack range from about -6 to 6 degrees at a Reynolds number per foot of approximately 4.0 x 10 to the 6th power. Results indicated that the complete configuration exhibited nonlinear variations of normal-force and pitching-moment coefficients with angle of attack which were attributed to the downwash field of the forward fins and its effects on the rear fins. The complete configuration was stable about the test center-of-gravity location which was close to the estimated fullscale-vehicle initial center-of-gravity location. (Author).

Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63
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:

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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.

Static Longitudinal Characteristics at High Subsonic Speeds of a Complete Airplane Model with a Highly Tapered Wing Having the 0.80 Chord Line Unswept and with Several Tail Configurations
Static Longitudinal Characteristics at High Subsonic Speeds of a Complete Airplane Model with a Highly Tapered Wing Having the 0.80 Chord Line Unswept and with Several Tail Configurations

Author: Kenneth W. Goodson

Publisher:

Published: 1961

Total Pages: 64

ISBN-13:

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An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.