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: 80
ISBN-13:
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Author: Thomas C. Kelly
Publisher:
Published: 1962
Total Pages: 80
ISBN-13:
DOWNLOAD EBOOKAuthor: Thomas C. Kelly
Publisher:
Published: 1962
Total Pages: 1
ISBN-13:
DOWNLOAD EBOOKResults 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).
Author: Lloyd S. Jernell
Publisher:
Published: 1963
Total Pages: 40
ISBN-13:
DOWNLOAD EBOOKAuthor: Robert J. Keynton
Publisher:
Published: 1971
Total Pages: 60
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DOWNLOAD EBOOKResults 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: Ross B. Robinson
Publisher:
Published: 1961
Total Pages: 42
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DOWNLOAD EBOOKAuthor: Lloyd S. Jernell
Publisher:
Published: 1961
Total Pages: 32
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DOWNLOAD EBOOKAuthor: Kenneth W. Goodson
Publisher:
Published: 1961
Total Pages: 64
ISBN-13:
DOWNLOAD EBOOKAn 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.
Author: Bernard Spencer
Publisher:
Published: 1959
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOKAuthor: David E. Jr Reese
Publisher:
Published: 1960
Total Pages: 98
ISBN-13:
DOWNLOAD EBOOKAuthor: Thomas C. Kelly
Publisher:
Published: 1961
Total Pages: 68
ISBN-13:
DOWNLOAD EBOOKAerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angle-of-attack range from -8° to 8° at an average test Reynolds number per foot of about 4.0 x 106. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carryover from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number.